Apparatus for generating horizontal forces in aerial vehicles and related method

• US 20070095971A1
• Filed: 06/06/2006
• Published: 05/03/2007
• Est. Priority Date: 06/07/2005
• Status: Active Grant

• Current Assignee: Urban Aeronautics Ltd.
• Original Assignee: Urban Aeronautics Ltd.
• Inventors: Yoeli, Raphael
• Granted Patent: US 7,717,368 B2
• Time in Patent Office: Days
• US Class Current: 244/12.5
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 50/14 ducted or shrouded

Abstract

A vehicle, comprising: a vehicle frame; a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid through from an inlet at the upper end of the duct through an exit at the lower end of the duct, and thereby produce an upward lift force applied to the vehicle; a first plurality of substantially parallel, spaced vanes non-pivotally mounted across at least the inlet end of the duct; and fluidic means for affecting the ambient fluid flow around the vanes to generate horizontal force components to the lift force applied to the vehicle.

Claims

1. A vehicle, comprising:

a vehicle frame;

a duct carried by said vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame;

a propeller rotatably mounted within said duct about the longitudinal axis of the duct to force an ambient fluid from an inlet at the upper end of the duct through an exit at the lower end of the duct, and thereby produce an upward lift force applied to the vehicle; and

a first plurality of parallel, spaced vanes non-pivotally mounted across at least the inlet end of the duct; and

fluidic means for affecting said ambient fluid flow around said vanes to generate horizontal force components to the lift force applied to the vehicle.

2. The vehicle of claim 1 wherein said vanes have an airfoil-shaped cross section.

3. The vehicle of claim 1 wherein said vanes have an elliptical cross section.

4. The vehicle of claim 1 and comprising a second plurality of parallel spaced vanes non-pivotally mounted across an exit end of said duct.

5. The vehicle of claim 1 wherein said first plurality of vanes extend substantially parallel to said longitudinal axis of said vehicle frame.

6. The vehicle of claim 1 wherein said second plurality of vanes extend substantially parallel to said longitudinal axis of said vehicle frame.

7. The vehicle of claim 1 wherein at least some of said first plurality of vanes are twisted at outer ends thereof.

8. The vehicle of claim 4 wherein at least some of said second plurality of vanes are twisted at outer ends thereof.

9. The vehicle of claim 1 wherein said first plurality of vanes is divided into first and second groups of parallel vanes, each group making an angle of substantially 45°

to the longitudinal axis of the vehicle frame, with the first group extending at an angle of substantially 90°

to the second group.

10. A ducted propulsion unit for a VTOL vehicle, the propulsion unit comprising:

a duct having an interior defined by a peripheral wall, inlet end and an exit end;

a propeller located in said duct interior axially between said inlet end and said exit end;

at least a first plurality of non-pivotal, substantially parallel spaced vanes extending across the inlet end; and

at least one fluidic control device located in proximity to said first plurality of vanes for affecting fluid flow about one or more of said first plurality of vanes.

11. The vehicle of claim 10 wherein said fluidic control device comprises a piezoelectric actuator located on a peripheral wall of said duct, adjacent a chamber in said peripheral wall, said chamber in fluid communication with said duct interior.

12. The vehicle of claim 11 and comprising a second plurality of substantially parallel spaced vanes non-pivotally mounted across an exit end of said duct;

and

further comprising at least another piezoelectric actuator located in proximity to said second plurality of vanes.

13. The vehicle of claim 10 wherein said fluid control device is capable of applying a vacuum in proximity to one or more of said first plurality of vanes.

14. The vehicle of claim 10 wherein said fluid control device is capable of supplying pressurized air in proximity to one or more of said first plurality of vanes.

15. A method of generating horizontal forces in a ducted propulsion unit of a VTOL vehicle comprising:

(a) arranging at least one duct in a frame of the vehicle, the duct having inlet and exit ends, with a propeller mounted within the duct between the ends;

(b) securing a plurality of non-pivotal vanes across at least the inlet end of the duct; and

(c) affecting air flow about said plurality of non-pivotal vanes to create horizontal control forces on the vehicle.

16. The method of claim 15 wherein step (c) is carried out by applying suction through apertures in a peripheral wall of the duct or in at least some of said plurality of vanes.

17. The method of claim 15 wherein step (c) is carried out by applying air under pressure through apertures in a peripheral wall of the duct or in at least some of said plurality of vanes.

18. The method of claim 15 wherein step (c) is carried out by utilizing piezoelectric actuators to generate periodically alternating pressure pulses at the inlet end of said duct.

19. The method of claim 15 wherein step (b) includes securing a second plurality of non-pivotal vanes across the exit end of the duct.

20. The method of claim 19 wherein step (c) includes affecting air about the second plurality of non-pivotal vanes.

21. The method of claim 18 wherein said piezoelectric actuator is located adjacent a cavity in a peripheral wall at the inlet end of said duct, such that pressure pulses generated by said actuator emanate from said cavity into the air flowing into the duct at the inlet end thereof.

22. The method of claim 21 wherein the pressure pulses emanate into the air at a location between leading and trailing edges of the vanes.