Tiltrotor aircraft having rotatable wing extensions

Patent metadata

Field	Value
Publication number	US-10011349-B2
Application number	US-201615252545-A
Country	US
Kind code	B2
Filing date	Aug 31, 2016
Priority date	Aug 31, 2016
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

First claim

What is claimed is:

1. A pylon assembly for a tiltrotor aircraft comprising:
a fixed pylon having an outboard end;
a rotor assembly rotatably coupled to the fixed pylon and operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode, the rotor assembly including a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode; and
a wing extension rotatably coupled to the outboard end of the fixed pylon, the wing extension having a minimal dimension;
wherein, the wing extension is operable to rotate generally with the rotor assembly such that the minimal dimension of the wing extension remains in the slipstream of the proprotor.

2. The pylon assembly as recited in claim 1 further comprising a linkage arm at least partially disposed in the fixed pylon, the linkage arm transferring a rotational force of the rotor assembly to the wing extension.

3. The pylon assembly as recited in claim 2 wherein the linkage arm further comprises a first end and a second end, the first end of the linkage arm coupled to the rotor assembly, the second end of the linkage arm coupled to the wing extension.

4. The pylon assembly as recited in claim 3 wherein the rotor assembly further comprises a mast, the first end of the linkage arm coupled to the mast.

5. The pylon assembly as recited in claim 3 further comprising a wing extension shaft at least partially extending through the fixed pylon, the second end of the linkage arm coupled to the wing extension shaft.

6. The pylon assembly as recited in claim 5 wherein the wing extension shaft has an outboard end fixedly coupled to a quarter chord point of the wing extension.

7. The pylon assembly as recited in claim 5 wherein the wing extension shaft has an inboard end rotatably coupled to an anchoring component at least partially located in the fixed pylon.

8. The pylon assembly as recited in claim 7 wherein the anchoring component further comprises a gearbox.

9. The pylon assembly as recited in claim 1 further comprising an actuator operable to rotate the wing extension.

10. The pylon assembly as recited in claim 1 wherein the fixed pylon further comprises a nacelle, the nacelle including an engine and at least one gearbox.

11. The pylon assembly as recited in claim 1 wherein axes of rotation of the rotor assembly and the wing extension are substantially coaxial.

12. The pylon assembly as recited in claim 1 wherein axes of rotation of the rotor assembly and the wing extension are non-coaxial.

13. The pylon assembly as recited in claim 1 wherein the rotor assembly and the wing extension form substantially congruent pitch angles relative to the fixed pylon while rotating through a range of motion.

14. The pylon assembly as recited in claim 1 wherein the rotor assembly and the wing extension form different pitch angles relative to the fixed pylon while rotating through a range of motion.

15. The pylon assembly as recited in claim 1 wherein the rotor assembly and the wing extension are rotatable, in synchrony, between the generally vertical orientation in the vertical takeoff and landing mode and the generally horizontal orientation in the forward flight mode.

16. A tiltrotor aircraft comprising:
a fuselage;
first and second wings supported by the fuselage, the first and second wings each having an outboard end; and
first and second pylon assemblies positioned, respectively, proximate the outboard ends of the first and second wings, each of the pylon assemblies including:
a fixed pylon having an outboard end;
a rotor assembly rotatably coupled to the fixed pylon and operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode, the rotor assembly including a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode; and
a wing extension rotatably coupled to the outboard end of the fixed pylon, the wing extension having a minimal dimension;
wherein, the wing extension is operable to rotate generally with the rotor assembly such that the minimal dimension of the wing extension remains in the slipstream of the proprotor.

17. The tiltrotor aircraft as recited in claim 16 wherein each of the pylon assemblies further comprises a linkage arm at least partially disposed in the fixed pylon, the linkage arm transferring a rotational force of the rotor assembly to the wing extension.

18. The tiltrotor aircraft as recited in claim 16 wherein each of the pylon assemblies further comprises an actuator operable to rotate the wing extension.

19. The tiltrotor aircraft as recited in claim 16 wherein, for each pylon assembly, axes of rotation of the rotor assembly and the wing extension are substantially coaxial.

20. The tiltrotor aircraft as recited in claim 16 wherein, for each pylon assembly, the rotor assembly and the wing extension are rotatable, in synchrony, between the generally vertical orientation in the vertical takeoff and landing mode and the generally horizontal orientation in the forward flight mode.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Ivans Steven Ray
• Wu Nathan Gabriel

Classifications

• B64C3/38

  Adjustment of complete wings or parts thereof · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/00

  Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft · CPC title

• B64C7/02

  Nacelles · CPC title

• B64C5/16

  about spanwise axes · CPC title