Counter torque device

Patent metadata

Field	Value
Publication number	US-11072422-B2
Application number	US-201816004375-A
Country	US
Kind code	B2
Filing date	Jun 9, 2018
Priority date	Jun 9, 2018
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.

First claim

What is claimed is:

1. A helicopter, comprising:
a fuselage comprising a main rotor;
a tail boom extending from the fuselage and comprising a tail rotor; and
at least one counter torque device configured to provide counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated;
wherein the at least one counter torque device comprises a plate disposed on a bottom side of the fuselage; and
wherein the at least one counter torque device is selectively retractable into and deployable from the fuselage.

2. The helicopter of claim 1 , wherein the at least one counter torque device comprises a thrust fan disposed on opposing sides of the fuselage and configured to produce thrust in opposing directions.

3. The helicopter of claim 1 , wherein the at least one counter torque device comprises thrust fans disposed on opposing sides of the tail boom, each thrust fan being coupled to the tail boom by a horizontal stabilizer.

4. The helicopter of claim 3 , wherein each thrust fan comprises a housing having at least one duct disposed therethrough, and an associated thrust rotor disposed within the duct.

5. The helicopter of claim 4 , wherein the housings comprise vertical stabilizers that are offset laterally from a longitudinal axis of the fuselage and coupled to the tail boom by a horizontal stabilizer.

6. The helicopter of claim 5 , wherein the housings are radially aligned with the rotational axis of the main rotor.

7. The helicopter of claim 5 , wherein the housings are aligned parallel to the longitudinal axis of the fuselage, and wherein each thrust rotor is selectively pivotable to align radially with the rotational axis of the main rotor.

8. The helicopter of claim 1 , wherein at least one thrust device is configured to prevent rotation of the fuselage during sideward flight or equivalent crosswind conditions.

9. The helicopter of claim 8 , wherein the at least one thrust device provides sufficient counter torque to reduce the power demand of the tail rotor during sideward flight or equivalent crosswind conditions.

10. A helicopter, comprising:
a fuselage comprising a main rotor;
a tail boom extending from the fuselage and comprising a tail rotor; and
at least one counter torque device configured to provide counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated;

wherein the at least one counter torque device comprises a thrust fan disposed on a bottom side of the fuselage.

11. The helicopter of claim 10 , wherein the at least one counter torque device is aligned with a longitudinal axis of the fuselage and disposed forward of a rotational axis of the main rotor.

12. The helicopter of claim 10 , wherein the at least one counter torque device is aligned with a longitudinal axis of the fuselage and disposed rearward of a rotational axis of the main rotor.

13. A method of operating a helicopter, comprising:
providing a helicopter comprising a fuselage having a main rotor, a tail boom extending from the fuselage and having a tail rotor, and at least one counter torque device;
operating the helicopter in at least one of hover and sideward flight;
operating the tail rotor to provide counter torque to the fuselage; and
providing additional counter torque to the fuselage with the at least one counter torque device to prevent counter rotation of the fuselage;
wherein the at least one counter torque device comprises at least one of a plate and a thrust fan disposed on a bottom side of the fuselage.

14. The method of claim 13 , further comprising: selectively deploying and retracting the at least one counter torque device.

15. The method of claim 13 , wherein the at least one counter torque device comprises thrust fans disposed on opposing sides of the tail boom, wherein each thrust fan comprises a housing having at least one duct disposed therethrough, and an associated thrust rotor disposed within the duct, and wherein the thrust fans are configured to provide propulsive force in forward flight.

16. The method of claim 15 , wherein the thrust fans are radially aligned with the rotational axis of the main rotor.

17. The method of claim 15 , further comprising: selectively pivoting the thrust fans to radially align the thrust fans with the rotational axis of the main rotor.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Sinusas Eric Albert
• Brand Albert Gerard

Classifications

• B64C5/00

  Stabilising surfaces · CPC title

• B64C2027/8236

  including pusher propellers · CPC title

• B64C5/12

  for retraction against or within fuselage or nacelle · CPC title

• B64C2027/8254

  Shrouded tail rotors, e.g. "Fenestron" fans · CPC title

• B64C2027/8281

  comprising horizontal tail planes · CPC title