A TRANSITION ARRANGEMENT FOR AN AIRCRAFT

• US 20160052618A1
• Filed: 04/14/2014
• Published: 02/25/2016
• Est. Priority Date: 04/15/2013
• Status: Active Grant

• Current Assignee: Christian Emmanuel Norden
• Original Assignee: Christian Emmanuel Norden
• Inventors: Norden, Christian Emmanuel
• Granted Patent: US 9,902,486 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 3/385 Variable incidence wings

Abstract

According to the invention there is provided a transition arrangement (10) for an aircraft for aiding stabilization of an aircraft between substantially vertical and horizontal flight of the aircraft, the transition arrangement (10) including an aerofoil (12) and mounting means for mounting the aerofoil rotatable between a leading (18) and/or a trailing edge (20) of an aircraft wing.

Claims

1. A transition arrangement for an aircraft for aiding stabilization of an aircraft between substantially vertical and horizontal flight of the aircraft, the transition arrangement including:

—

an aerofoil; and

a mounting means for mounting the aerofoil rotatably between a leading and a trailing edge of an aircraft wing.

2. A transition arrangement as claimed in claim 1 wherein the aerofoil includes a leading and trailing edge.

3. A transition arrangement as claimed in claim 1 wherein the aerofoil is mounted adjacent a static wing trailing edge.

4. A transition arrangement as claimed in claim 1 wherein the aerofoil is mounted adjacent a static wing leading edge.

5. A transition arrangement as claimed in claim 2 wherein the transition arrangement is mounted on a tail wing of the aircraft.

6. A transition arrangement as claimed in claim 2, wherein the leading and trailing edges are pivotally connected to the aircraft.

7. A transition arrangement as claimed in claim 1 including a rotary drive means for rotating the aerofoil via the mounting means, when in operation.

8. A transition arrangement as claimed in claim 1 wherein the mounting means is in the form of a primary shaft extending longitudinally the wing from a distal wing tip region towards a proximal region, the wing extending from a fuselage of the aircraft.

9. A transition arrangement as claimed in claim 8 wherein the primary shaft is rotatable.

10. A transition arrangement as claimed in claim 8 wherein the mounting means includes a plurality of secondary shafts which are connected to the primary shaft or shaft mount in a substantially parallel spaced relationship relative thereto.

11. A transition arrangement as claimed in claim 10 wherein the primary and secondary shafts are interconnected via linkages for allowing the primary and secondary shafts to be rotatable relative to one another.

12. A transition arrangement as claimed in claim 8 wherein the wing is rotatable about the primary shaft.

13. A transition arrangement as claimed in claim 8 wherein aerofoils are mounted rotatably to the secondary shaft.

14. A transition arrangement as claimed in claim 13, wherein the aerofoils mounted rotatably to the secondary shafts, together with a centre part of the wing creates a substantially conventional wing chord-wise profile for non-rotating conventional level fuel-saving flight or a substantial Z or S profile for wing rotation—

engine-powered or airflow-driven autorotation for (near-) vertical flight or emergencies.

15. An aircraft including a transition arrangement as claimed in claim 1 said aircraft including:

a fuselage with wings attached thereto;

ailerons and elevators arranged onto the wings; and

propulsion means arranged onto the aircraft to facilitate vertical and/or horizontal flight.

16. An aircraft as claimed in claim 15 wherein the propulsion means is in the form of any one or more selected from the groups consisting of a propeller, rotor, fan, and/or jet engine.

17. An aircraft as claimed in claim 15 wherein the wings are adapted for rotation, the speed of rotation and/or foil profile of one or more rotating wings can be continually adjusted relative to the other(s) to create greater flight stability, especially in vertical flight to be enhanced by a vertical lift system, e.g., an articulated rotor or set of rotors;

stability created by the continuous balancing of drag-lift forces created by the rotating aerofoils, combined with the balancing of the engine-powered direct lift forces.

18. (canceled)

19. (canceled)

20. (canceled)

21. (canceled)

22. (canceled)

23. (canceled)

24. (canceled)