System and method for assisting in rotor speed control

Patent metadata

Field	Value
Publication number	US-9821908-B2
Application number	US-201414297136-A
Country	US
Kind code	B2
Filing date	Jun 5, 2014
Priority date	Jun 7, 2013
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

First claim

The invention claimed is:

1. A system of assisting in rotor speed control in a rotorcraft, the system comprising:
a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit;
wherein the lower droop limit is below a normal lower rotor speed range; and
wherein the actuator is a collective actuator configured to cause a pitch change in a rotor blade as a function of the decrease collective command to provide an initial increase in rotor speed.

2. The system according to claim 1 , wherein the control law is operable to generate the decrease collective command without the detection of an engine failure.

3. The system according to claim 1 , further comprising:
a sensor configured for measuring the rotor speed.

4. The system according to claim 1 , wherein the lower droop limit is a function of a difference between a commanded rotor speed and the rotor speed.

5. The system according to claim 1 , wherein the computer is further operable to at least partially remove collective command authority from a vertical loops control law, the vertical loops control law being configured to make collective commands so that the rotorcraft can hold a desired vertical axis state.

6. The system according to claim 1 , wherein the computer is a flight control computer located in the rotorcraft.

7. The system according to claim 1 , wherein the rotor speed decreasing below the lower droop limit is due to an undetected engine failure.

8. The system according to claim 1 , wherein the rotor speed decreasing below the lower droop limit is due to a pilot commanded pitch-up maneuver.

9. A method of assisting in rotor speed control in a rotorcraft, the method comprising:
measuring a rotor speed with a sensor;
detecting a droop in the rotor speed beyond a lower droop limit; and
commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit;
controlling a collective actuator to cause a pitch change in a rotor blade as a function of the commanded decrease in collective to provide an initial increase in rotor speed.

10. The method according to claim 9 , wherein the lower droop limit is below a normal lower rotor speed range.

11. The method according to claim 9 , wherein the lower droop limit is a function of a difference between a commanded rotor speed and an actual rotor speed.

12. The method according to claim 9 , further comprising:
at least partially removing collective command authority from a vertical loops control law.

13. The method according to claim 9 , further comprising:
switching collective command authority to an all engine inoperative control law after a detection of an engine failure.

14. The method according to claim 9 , wherein the step of detecting the droop in the rotor speed beyond the lower droop limit is performed by a computer.

15. The method according to claim 9 , wherein the step of commanding the decrease in collective in response to the rotor speed drooping beyond the lower droop limit includes communicating a command to a collective actuator.

16. The method according to claim 9 , wherein the droop in the rotor speed beyond a lower droop limit is due to an undetected engine failure.

17. The method according to claim 9 , further comprising:
adjusting the lower droop limit according to an altitude of the rotorcraft.

18. The method according to claim 9 , wherein the lower droop limit is adjusted higher at lower altitudes and adjusted lower at higher altitudes.

19. The method according to claim 9 , wherein a magnitude of the decrease in collective has a nonlinear relationship to an amount of the rotor speed drooping beyond the lower droop limit, such that the magnitude of the decrease in collective exponentially increases as the amount of the rotor speed drooping beyond the lower droop limit increases.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Schaeffer Joseph M
• Patel Jignesh
• O'Neill Eric

Classifications

• G05D1/0858

  specially adapted for vertical take-off of aircraft · CPC title

• B64C27/57 Primary

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title

• B64C27/46

  Blades · CPC title