System and method for tail rotor margin awareness

Patent metadata

Field	Value
Publication number	US-10315779-B2
Application number	US-201715708767-A
Country	US
Kind code	B2
Filing date	Sep 19, 2017
Priority date	Sep 19, 2017
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.

First claim

What is claimed is:

1. A rotorcraft comprising:
tail rotor blades;
a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator;
pilot flight controls electrically coupled to the tail rotor actuator such that the current extension of the tail rotor actuator varies according to input from the pilot flight controls; and
a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to:
determine the current extension of the tail rotor actuator;
determine whether the current extension of the tail rotor actuator is within a margin of an extension limit of the tail rotor actuator; and
indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the extension limit of the tail rotor actuator.

2. The rotorcraft of claim 1 , further comprising:
a sensor coupled to the tail rotor actuator, wherein the flight control computer is configured to determine the current extension of the tail rotor actuator by measuring the current extension of the tail rotor actuator with the sensor.

3. The rotorcraft of claim 1 , further comprising:
an instrument panel, the flight control computer further configured to indicate the first warning with a visual cue at the instrument panel.

4. The rotorcraft of claim 3 , wherein the visual cue is color coded based upon an extent of the current extension within the margin.

5. The rotorcraft of claim 1 , further comprising:
an intercom, the flight control computer further configured to indicate the first warning with a first audio cue through the intercom.

6. The rotorcraft of claim 5 , wherein the first audio cue is the same as a second audio cue used to indicate a second warning through the intercom.

7. The rotorcraft of claim 5 , wherein the first audio cue is different from a second audio cue used to indicate a second warning through the intercom.

8. The rotorcraft of claim 1 , wherein the pilot flight controls include a pedal electrically coupled to the tail rotor actuator.

9. The rotorcraft of claim 8 , wherein the pedal comprises a trim motor, the first warning indicated with haptic feedback through the trim motor.

10. The rotorcraft of claim 1 , wherein the pilot flight controls include a beep switch electrically coupled to the tail rotor actuator.

11. The rotorcraft of claim 1 , wherein the margin is 10% of the extension limit of the tail rotor actuator.

12. The rotorcraft of claim 1 , wherein the flight control computer is configured to determine whether the current extension of the tail rotor actuator is within the margin of the extension limit of the tail rotor actuator by:
calculating a difference between the extension limit of the tail rotor actuator and the current extension of the tail rotor actuator; and
determining whether the difference is less than the margin.

13. The rotorcraft of claim 1 , wherein the flight control computer is configured to determine whether the current extension of the tail rotor actuator is within the margin of the extension limit of the tail rotor actuator by:
determining whether the current extension of the tail rotor actuator is greater than a predetermined value.

14. The rotorcraft of claim 1 , wherein the flight control computer is further configured to vary the pitch of the tail rotor blades independent of the input from the pilot flight controls.

15. The rotorcraft of claim 14 , further comprising:
aircraft sensors, the flight control computer further configured to vary the pitch of the tail rotor blades according to environmental conditions measured by the aircraft sensors.

16. The rotorcraft of claim 1 , further comprising:
a rotor system to generate aerodynamic lift, the rotor system producing torque in a first direction; and
an anti-torque system comprising the tail rotor blades and the tail rotor actuator, the anti-torque system producing torque in a second direction opposite the first direction.

17. A method of flying a rotorcraft, the method comprising:
sensing, by a flight control computer (FCC) of the rotorcraft, a current extension of a tail rotor actuator coupled to tail rotor blades of the rotorcraft;
determining, by the FCC, whether the current extension of the tail rotor actuator is within a margin of an extension limit of the tail rotor actuator;
indicating, by the FCC, a warning to a pilot of the rotorcraft in response to determining the current extension of the tail rotor actuator is within the margin of the extension limit of the tail rotor actuator; and
transmitting, by the FCC, a control signal to the tail rotor actuator, the tail rotor actuator being electrically coupled to the FCC such that the current extension of the tail rotor actuator varies according to the control signal from the FCC.

18. The method of claim 17 , wherein the determining step is instituted in response to detecting a change in position of a pilot flight control of the rotorcraft.

19. The method of claim 17 , wherein the determining step is instituted in response to the control signal being generated by the FCC to change the current extension of the tail rotor actuator.

20. The method of claim 17 , wherein determining whether the current extension of the tail rotor actuator is within the margin of the extension limit of the tail rotor actuator comprises:
calculating a difference between the extension limit of the tail rotor actuator and the current extension of the tail rotor actuator; and
determining whether the difference is less than the margin.

21. The method of claim 17 , wherein determining whether the current extension of the tail rotor actuator is within the margin of the extension limit of the tail rotor actuator comprises:
determining whether the current extension of the tail rotor actuator is greater than a predetermined value.

22. The method of claim 17 , wherein transmitting the control signal to the tail rotor actuator comprises:
sensing, by the FCC, flight conditions of the rotorcraft;
calculating, by the FCC, a desired extension of the tail rotor actuator to achieve or maintain a desired flight attitude; and
transmitting, by the FCC, independently of a pilot command, the control signal to move the tail rotor actuator to the desired extension.

23. A method of flying a rotorcraft, the method comprising:
detecting input from a pilot flight control of the rotorcraft;
sensing a current extension of a tail rotor actuator coupled to tail rotor blades of the rotorcraft, the tail rotor actuator being electrically coupled to the pilot flight control such that the current extension of the tail rotor actuator varies according to the input from the pilot flight control;
determining whether actuating the tail rotor actuator according to the input from the pilot flight control would cause an updated extension of the tail rotor actuator to be within a margin of an extension limit of the tail rotor actuator; and
indicating a warning to a pilot of the rotorcraft in response to determining the updated extension of the tail rotor actuator will be within the margin of the extension limit of the tail rotor actuator.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Bothwell Christopher M
• Worsham Ii Robert Earl
• Kim Sung Kyun
• Thomas Brandon Jeffrey

Classifications

• B64C27/78

  in association with pitch adjustment of blades of anti-torque rotor · CPC title

• B64C27/68

  using electrical energy, e.g. having electrical power amplification · CPC title

• B64C13/10

  comprising warning devices · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64D45/0005 Primary

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title