WALL EFFECTS ON VTOL VEHICLES

• US 20100051753A1
• Filed: 11/27/2007
• Published: 03/04/2010
• Est. Priority Date: 11/27/2006
• Status: Active Grant

• Current Assignee: Urban Aeronautics Ltd.
• Original Assignee: Urban Aeronautics Ltd.
• Inventors: Yoeli, Raphael
• Granted Patent: US 8,833,692 B2
• Time in Patent Office: Days
• US Class Current: 244/23.A
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage

Abstract

ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams.

Claims

1. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air with normally symmetrical airflow streams into said duct through an inlet at an upper end of said duct, thereby creating a lift force;

a plurality of vanes extending across said inlet, substantially parallel to said longitudinal axis; and

wherein one or more of said vanes are selectively pivotable to align with adjacent asymmetrical airflow streams.

2. The vehicle of claim 1 and further comprising one or more sensors that monitor an angle of attack of airflow streams striking said vanes.

3. The vehicle of claim 2 wherein said one or more sensors comprise one or more transducers attached to one or more of said vanes.

4. The vehicle of claim 3 wherein at least one transducer is attached to a vane section independently pivotable relative to one or more remaining vane sections.

5. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force directed substantially along a duct axis;

a plurality of pivotably adjustable vanes extending across said inlet, substantially parallel to said longitudinal axis; and

means for maintaining at least some of said plurality of vanes substantially parallel to airflow streams entering said inlet.

6. A method of operating a ducted air flow vehicle comprising a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force directed substantially along a duct axis;

a plurality of adjustable vanes extending across said inlet, substantially parallel to said longitudinal axis, the method comprising;

(a) determining an angle of attack of airflow streams striking said vanes;

and

(b) adjusting at least some of said vanes to maintain said angle of attack at substantially zero.

7. The method of claim 6 wherein step (a) is carried out using one or more sensors attached to one or more of said vanes.

8. The method of claim 6 wherein step (a) is carried out by pre-mapping airflow stream lines in various flight conditions.

9. The method of claim 6 wherein said step (a) is carried out substantially in real time.

10. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one forward duct and one aft duct, each having a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force; and

at least one separator on at least one side of the vehicle and moveable between retracted and extended positions, said separator adapted to prevent the vehicle from being drawn to an adjacent object.

11. The vehicle of claim 10 wherein the vehicle includes a payload bay and wherein said separator retracts into said payload bay.

12. The vehicle of claim 10 wherein the vehicle includes a payload bay and wherein said separator retracts to a location below said payload bay.

13. The vehicle of claim 10 wherein said separator is provided with a bumper at a remote end thereof.

14. The vehicle of claim 10 wherein said separator comprises one or more plates provided with a perforated surface.

15. The vehicle of claim 10 wherein said separator comprises a ramp capable of supporting one or more people.

16. The vehicle of claim 10 wherein said separator comprises a plurality of plates along said one side of said fuselage.

17. The vehicle of claim 16 wherein said plurality of plates include plates adjacent said front and rear ducts.

18. The vehicle of claim 17 wherein said plates adjacent said front and rear ducts are moveable to said retracted position by a folding or tilting movement.

19. The vehicle of claim 10 wherein said separator comprises at least one inflatable bag.

20. The vehicle of claim 10 wherein said separator comprises at least one inflatable tubular member extending alongside the fuselage.

21. The vehicle of claim 20 wherein said at least one inflatable tubular member comprises an array of said tubular members.

22. The vehicle of claim 10 wherein said separator further comprises one or more flexible tubular members partially or substantially completely surrounding said fuselage.

23. The vehicle of claim 10 wherein said separator includes one or more landing gear components moveable from a substantially vertical landing position to a substantially horizontal separator position.

34. The vehicle of claim 19 further comprising at least one thruster fan and wherein said injectable bag is located so as to protect said thruster fan in the vent of engagement with the object.

24. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one forward duct and one aft duct, each having a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force;

a plurality of vanes extending across said inlet of each of said ducts, substantially parallel to said longitudinal axis;

wherein one or more groups of said vanes are selectively pivotable to align with airflow streams entering said ducts; and

at least one separator located along and extending from at least one side of the fuselage, said separator adapted to prevent the vehicle from being drawn to an adjacent wall surface in a substantially hover mode.

25. The vehicle of claim 24 wherein said separator is movable between extended and retracted positions.

26. A ducted flow vehicle comprising:

a fuselage having a longitudinal axis and supporting front and rear airflow ducts, each having a prime mover arranged to force surrounding air into said duct through an inlet at an upper end thereof thereby creating a lifting force directed substantially along said duct axis and wherein said ducts are formed with open areas along opposite sides of said fuselage for reducing sensitivity to side winds.

27. The vehicle of claim 26 wherein said open areas comprise adjustable openings in walls forming said ducts.

28. The vehicle of claim 26 wherein each duct is provided with inlet and outlet vanes and wherein said openings are between planes containing said inlet and outlet vanes.

29. The vehicle of claim 26 wherein a plurality of adjustable vanes extend across said inlets of said ducts and wherein at least some of said vanes are pivotably adjustable to an orientation substantially parallel with air streams entering said ducts.

30. The vehicle of claim 29 wherein said vehicle is provided with at least one separator extending outwardly from a side of said fuselage for maintaining said vehicle laterally spaced from an adjacent fixed surface in a hover mode.

31. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one forward duct and one aft duct, each having a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force; and

a fender installed at the inlet side of the duct to allow air to flow into the duct inlet but prevent damage from debris or flying objects.

32. The vehicle of claim 31 wherein said fender comprises a perforated device.

33. The vehicle of claim 31 wherein the fender is located at distance from the duct.

35. A ducted air flow vehicle comprising:

a fuselage having a longitudinal axis, supporting at least one forward duct and one aft duct, each having a prime mover arranged to force surrounding air into said duct through an inlet at an upper end of said duct thereby creating a lift force; and

at least one separator on at least one side of the vehicle and moveable between respective positions protecting the vehicle upon engagement with an object or surface horizontally or vertically.