Tail rotor assembly

Patent metadata

Field	Value
Publication number	US-11148796-B2
Application number	US-201816007666-A
Country	US
Kind code	B2
Filing date	Jun 13, 2018
Priority date	Jun 13, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.

First claim

What is claimed is:

1. A helicopter, comprising:
a fuselage;
a tail boom extending from the fuselage;
a main rotor system; and
a tail rotor assembly disposed on an aft end of the tail boom, comprising:
a tail rotor housing; and
at least one substantially vertical ducted fan disposed in the tail rotor housing and configured to generate anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated; and
at least one canted ducted fan disposed in the tail rotor housing and configured to generate both anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated and lift to the tail boom in order to control pitch of the helicopter;
wherein the at least one substantially vertical ducted fan and the at least one canted ducted fan comprise axes of rotations that are substantially fixed relative to each other.

2. The helicopter of claim 1 , wherein the at least one substantially vertical ducted fan and the at least one canted ducted fan are electric fans.

3. The helicopter of claim 1 , wherein the tail rotor housing comprises an upper normal section comprising at least one substantially vertical ducted fan, a middle canted section comprising the at least one canted ducted fan, and a lower normal section comprising at least one substantially vertical ducted fan.

4. The helicopter of claim 1 , wherein the tail rotor housing comprises an upper canted section comprising at least one canted ducted fan, a middle normal section comprising the at least one substantially vertical ducted fan, and a lower canted section comprising at least one canted ducted fan.

5. The helicopter of claim 1 , wherein a rotational speed of the at least one substantially vertical ducted fan and the at least one canted ducted fan are independently controlled.

6. The helicopter of claim 5 , wherein the at least one substantially vertical ducted fan and at least one canted ducted fan are controlled by at least one of (1) manually by a pilot of the helicopter and (2) automatically by a control system of the helicopter.

7. The helicopter of claim 6 , wherein the at least one substantially vertical ducted fan and the at least one canted ducted fan are at least one of (1) automatically controlled in response to the center of gravity of the helicopter and (2) initiated by a pilot to control pitch attitude of the helicopter.

8. The helicopter of claim 6 , wherein when additional lift to the tail boom is required to pitch the helicopter forward, thrust generated by the at least one canted ducted fan is increased and thrust generated by the at least one substantially vertical ducted fan is decreased to maintain a required level of anti-torque thrust.

9. The helicopter of claim 8 , wherein generating additional lift with the at least one canted ducted fan while maintaining the required level of anti-torque thrust increases payload capacity of the helicopter.

10. The helicopter of claim 9 , wherein the at least one canted ducted fan is configured to generate sufficient lift to the tail boom in order to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system.

11. The helicopter of claim 10 , wherein the at least one canted ducted fan is configured to generate sufficient lift to the tail boom in order to orient the helicopter in a nose-down orientation.

12. A tail rotor assembly for a helicopter, comprising:
a tail rotor housing; and
at least one substantially vertical ducted fan disposed in the tail rotor housing and configured to generate anti-torque thrust; and
at least one canted ducted fan disposed in the tail rotor housing and configured to generate both anti-torque thrust and lift to a tail boom in order to control pitch of a helicopter;
wherein the at least one substantially vertical ducted fan and the at least one canted ducted fan comprise axes of rotations that are substantially fixed relative to each other.

13. The tail rotor assembly of claim 12 , wherein the number of substantially vertical ducted fans and the number of canted ducted fans are equal.

14. The tail rotor assembly of claim 12 , wherein a rotational speed of the at least one substantially vertical ducted fan and the at least one canted ducted fan are independently controlled at least one of (1) manually by a pilot of the helicopter and (2) automatically by a control system of the helicopter.

15. The tail rotor assembly of claim 14 , wherein when additional lift to the tail boom is required to pitch the helicopter forward, thrust generated by the at least one canted ducted fan is increased and thrust generated by the at least one substantially vertical ducted fan is decreased to maintain a required level of anti-torque thrust.

16. The tail rotor assembly of claim 15 , wherein the at least one canted ducted fan is configured to generate sufficient lift to the tail boom in order to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward.

17. The tail rotor assembly of claim 14 , wherein the at least one canted ducted fan is configured to generate sufficient lift to the tail boom in order to orient the helicopter in a nose-down orientation.

18. A method of operating a helicopter, comprising:
providing a helicopter with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly comprising a tail rotor housing, at least one substantially vertical ducted fan, and at least one canted ducted fan;
adding additional payload or shifting the payload that causes a shift in the center of gravity of the helicopter;
adjusting the thrust generated by the at least one canted ducted fan to alter lift to the tail boom of the helicopter while adjusting the thrust generated by the at least one substantially vertical ducted fan to regulate the amount of anti-torque thrust provided to the tail boom of the helicopter;
wherein the at least one substantially vertical ducted fan and the at least one canted ducted fan comprise axes of rotations that are substantially fixed relative to each other.

19. The method of claim 18 , wherein the adjusting the thrust generated by the at least one canted ducted fan and the adjusting the amount of thrust generated by the at least one substantially vertical ducted fan are at least one of (1) automatically initiated in response to a change in the center of gravity of the helicopter and (2) initiated by a pilot to control pitch attitude of the helicopter.

20. The method of claim 18 , further comprising: reducing the payload or shifting the payload that causes a forward shift in the center of gravity of the helicopter; and reducing the thrust generated by the at least one canted ducted fan to reduce lift to the tail boom of the helicopter while increasing the amount of thrust generated by the at least one substantially vertical ducted fan to maintain the amount of anti-torque thrust provided to the tail boom of the helicopter.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Brand Albert Gerard
• Sinusas Eric Albert

Classifications

• B64C27/82 Primary

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C2027/8218

  wherein the rotor or the jet axis is inclined with respect to the longitudinal horizontal or vertical plane of the helicopter · CPC title

• B64C2027/8227

  comprising more than one rotor · CPC title

• B64C2027/8254

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