VERTICAL TAKE-OFF AND LANDING AIRCRAFT

• US 20190270517A1
• Filed: 10/27/2017
• Published: 09/05/2019
• Est. Priority Date: 10/27/2016
• Status: Active Application

• Current Assignee: Veroplane Inc.
• Original Assignee: Mono Aerospace IP Ltd.
• Inventors: Morgan, Brian
• Application Number:
  US16/345,238
• Publication Number:
  US 20190270517A1
• Time in Patent Office: Days
• CPC Class Codes: B64C 11/001 Shrouded propellers
• CPC Class Codes: B64C 11/46 Arrangements of, or constructional features peculiar to, multiple propellers B64C11/306 takes precedence
• CPC Class Codes: B64C 23/06 by generating vortices
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/22 at the front of the wing
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 27/14 within, or attached to, fuselages
• CPC Class Codes: B64D 35/02 specially adapted for specific power plants
• CPC Class Codes: B64D 35/04 characterised by the transmission driving a plurality of propellers or rotors
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A lift rotor or ‘thrust’ system or assembly for a VTOL aircraft, comprising first and second lifting thrusters or rotors contained within a housing, the housing containing a leading edge, a trailing edge, a upper surface and a lower surface; wherein the housing includes one or more airflow manipulation devices provided on or associated with the housing configured to manage the airflow into or through at least one of the first and second rotors. In other aspects, the invention embraces an aircraft wing including a lift thruster system as defined above, and also an aircraft comprising such a lift thruster system.

Claims

1. A lift thruster system for a VTOL aircraft, comprising:

one or more lifting thrusters contained within a housing,

wherein the housing includes one or more airflow manipulation devices provided on or associated with the housing and configured to manage the airflow into or through at least one of the one or more lifting thrusters.

2. The lift thruster system of claim 1, wherein the one or more airflow manipulation devices comprises a spoiler located about an intake of at least one of the one or more lifting thrusters.

3. The lift thruster system of claim 2, wherein the spoiler is located on a leading edge of the housing.

4. The lift thruster system of any one of claim 1 or 2, wherein the spoiler is deployable between a stowed state and a deployed state in which it extends at an angle to a surrounding surface of the housing.

5. The lift thruster system of claim 4, wherein in the stowed position the spoiler lies flush with the surrounding surface of the housing.

6. The lift thruster system of any one of the preceding claims, further comprising one or more vortex generators located about an intake of at least one of the one or more lifting thrusters.

7. The lift thruster system of claim 6, wherein the vortex generators are defined by respective stubs protruding from the adjacent surface of the housing.

8. The lift thruster system of claim 7, including a plurality of vortex generators grouped into at least one pair.

9. The lift thruster system of claim 8, wherein each pair grouping of vortex generators are arranged in a V-shape.

10. The lift thruster system of claim 9, wherein for at least one of the groups the vortex generators are arranged such that the vertex of the pair points towards a leading edge of the housing.

11. The lift thruster system of claims 6 to 10, wherein the vortex generators are movable between deployed and stowed positions.

12. The lift thruster system of any preceding claim, further comprising a closure arrangement to selectively close or open at least one of the respective intake or outlet of the one or more lifting thrusters.

13. The lift thruster system of claim 12, wherein the closure arrangement comprises a deployable door that is slidable over the respective intake or outlet.

14. The lift thruster system of claim 12, wherein the deployable door comprises a flexible sheet that is deployable from a powered spool.

15. The lift thruster system of claim 13 or 14, wherein the deployable door is deployed automatically in dependent of the flight mode of an associated aircraft.

16. The lift thruster system of claims 12 to 15, wherein the deployable door is located at the intake of a respective one of the one or more lifting thrusters.

17. The lift thruster system of any of claims 12 to 16, wherein the closure arrangement includes a louver system.

18. The lift thruster system of claim 17, when dependent on claim 16, wherein the louver system is located at a respective outlet of at least one of the one or more lifting thrusters.

19. The lift thruster system of any one of claims 1 to 18, further comprising an air curtain system arranged about a respective intake of at least one of the one or more lifting thrusters.

20. The lift thruster system of claim 19, wherein the air curtain system comprises one or more ports extending about a respective intake of at least one of the one or more lifting thrusters.

21. The lift thruster system of claim 20, wherein the one or more ports includes a first port located forward of one of the thrusters and adjacent a leading edge of the housing.

22. The lift thruster system of claim 21, wherein the first port extends laterally across the housing in a width direction for a length that is about the same as the diameter of the intake of the respective thruster.

23. The lift thruster system of claim 22, wherein the first port is non-linear in plan view so as to define a forward portion.

24. The lift thruster system of claim 23, wherein the forward portion points towards the leading edge of the housing.

25. The lift thruster system of any one of the preceding claims, wherein the housing contains a plurality of lifting thrusters.

26. The lift thruster system of claim 25, wherein at least two of the plurality of lifting thrusters are arranged in a row.

27. The lift thruster system of claim 26, wherein the row is aligned in a fore-aft direction.

25-1. An aircraft wing including a lift thruster system as claimed in claims 1 to 24.

26-1. An aircraft comprising a lift thruster system as claimed in any one of claims 1 to 24.