Tiltrotor aircraft having active wing extensions

Patent metadata

Field	Value
Publication number	US-10279892-B2
Application number	US-201615252560-A
Country	US
Kind code	B2
Filing date	Aug 31, 2016
Priority date	Aug 31, 2016
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.

First claim

What is claimed is:

1. A propulsion and stabilization system for a tiltrotor aircraft comprising:
a wing having an outboard end;
a fixed pylon coupled to the outboard end of the wing, the fixed pylon including a rotor assembly rotatably coupled to an inboard portion of the fixed pylon;
a wing extension rotatably coupled to an outboard end of the fixed pylon such that an outboard portion of the fixed pylon is interposed between the rotor assembly and the wing extension;
an actuator coupled to the wing extension, the actuator operable to move the wing extension to dampen a mode of the wing;
a feedback loop computing unit in communication with the actuator, the feedback loop computing unit operable to control movement of the wing extension by the actuator; and
at least one sensor coupled to the wing and in data communication with the feedback loop computing unit, the at least one sensor operable to detect at least one stabilization parameter of the wing;
wherein the feedback loop computing unit is operable to determine a frequency of the mode of the wing based on the at least one stabilization parameter from the at least one sensor on the wing to form a detected frequency value;
wherein the feedback loop computing unit is operable to calculate a dampening frequency equal to the detected frequency value; and
wherein the feedback loop computing unit is operable to send a command including the dampening frequency to the actuator to oscillate the wing extension at the dampening frequency, thereby stabilizing the tiltrotor aircraft.

2. The propulsion and stabilization system as recited in claim 1 wherein the feedback loop computing unit is operable to determine a phase angle of the mode of the wing based on the at least one stabilization parameter.

3. The propulsion and stabilization system as recited in claim 2 wherein the feedback loop computing unit is operable to send the command to oscillate the wing extension at a different phase angle than the phase angle of the mode of the wing.

4. The propulsion and stabilization system as recited in claim 1 wherein the wing extension has oscillatory authority in a range of approximately 5 degrees to approximately −5 degrees.

5. The propulsion and stabilization system as recited in claim 1 wherein the dampening frequency is in a range of approximately 0.5 Hertz to approximately 10 Hertz.

6. The propulsion and stabilization system as recited in claim 1 wherein the wing extension is operable at a peak amplitude at greater than one frequency.

7. The propulsion and stabilization system as recited in claim 1 wherein the wing extension is oscillated using a springless actuation subsystem including the actuator.

8. The propulsion and stabilization system as recited in claim 1 wherein the outboard portion of the fixed pylon further comprises an engine, the engine interposed between the rotor assembly and the wing extension.

9. A tiltrotor aircraft comprising:
a fuselage;
first and second wings supported by the fuselage, the first and second wings each having an outboard end;
first and second fixed pylons coupled, respectively, to the outboard ends of the first and second wings, the first and second fixed pylons including first and second inboard rotor assemblies, respectively;
first and second wing extensions rotatably coupled, respectively, to outboard ends of the first and second fixed pylons such that an outboard portion of the first fixed pylon is interposed between the first rotor assembly and the first wing extension and an outboard portion of the second fixed pylon is interposed between the second rotor assembly and the second wing extension;
first and second actuators operable to move a respective one of the first and second wing extensions to dampen a mode of the wings;
a feedback loop computing unit in communication with the first and second actuators, the feedback loop computing unit operable to control movement of the first and second wing extensions by the first and second actuators; and
at least one sensor coupled to the wings and in data communication with the feedback loop computing unit, the at least one sensor operable to detect at least one stabilization parameter of the wings;
wherein the feedback loop computing unit is operable to determine a frequency of the mode of the wings based on the at least one stabilization parameter from the at least one sensor on the wings to form a detected frequency value;
wherein the feedback loop computing unit is operable to calculate a dampening frequency equal to the detected frequency value; and
wherein the feedback loop computing unit is operable to send a command including the dampening frequency to the first and second actuators to oscillate the first and second wing extensions at the dampening frequency, thereby stabilizing the tiltrotor aircraft.

10. The tiltrotor aircraft as recited in claim 9 wherein the first and second wing extensions have oscillatory authority in a range of approximately 5 degrees to approximately −5 degrees.

11. The tiltrotor aircraft as recited in claim 9 wherein the mode of the wings has a phase angle; and
wherein the first and second actuators are operable to oscillate the first and second wing extensions at a different phase angle than the phase angle of the mode of the wings such that the wings experience a dampening effect.

12. The tiltrotor aircraft as recited in claim 9 wherein the dampening frequency is in a range of approximately 0.5 Hertz to approximately 10 Hertz.

13. The tiltrotor aircraft as recited in claim 9 wherein the first and second rotor assemblies are rotatably coupled to inboard portions of the first and second fixed pylons, respectively.

14. A method for stabilizing a tiltrotor aircraft comprising:
receiving at least one stability parameter from at least one sensor coupled to a wing of the tiltrotor aircraft;
determining a frequency of a mode of the wing based on the at least one stability parameter from the at least one sensor on the wing to form a detected frequency value;
calculating a dampening frequency equal to the detected frequency value; and
sending a command including the dampening frequency to an actuator to oscillate a wing extension at the dampening frequency, thereby stabilizing the tiltrotor aircraft.

15. The method as recited in claim 14 wherein the command is sent from a feedback loop computing unit.

16. The method as recited in claim 14 wherein oscillating the wing extension at the dampening frequency to stabilize the tiltrotor aircraft further comprises moving the wing extension with approximately 5 degrees to approximately −5 degrees of oscillatory authority.

17. The method as recited in claim 14 wherein oscillating the wing extension at the dampening frequency to stabilize the tiltrotor aircraft further comprises oscillating the wing extension at a frequency in a range of approximately 0.5 Hertz to approximately 10 Hertz.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Bosworth Jeffrey

Classifications

• B64C13/18 Primary

  using automatic pilot · CPC title

• B64C3/385

  Variable incidence wings · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C7/02

  Nacelles · CPC title

• Y02T50/10

  Drag reduction · CPC title