System and method for assisting in rotor speed control

• US 10,392,105 B2
• Filed: 07/05/2017
• Issued: 08/27/2019
• Est. Priority Date: 06/07/2013
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Schaeffer, Joseph M., Patel, Jignesh, O'Neill, Eric
• Primary Examiner(s): Tissot, Adam D
• Assistant Examiner(s): Pipala, Edward J
• Application Number:
  US15/642,279
• Publication Number:
  US 20170297695A1
• Time in Patent Office: 783 Days
• CPC Class Codes: B64C 27/46 Blades
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

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.

Claims

1. A system for assisting in rotor speed control in a rotorcraft, the system comprising:

a sensor configured for measuring the rotor speed; and

a computer having a droop protection loop, the droop protection loop configured to detect a drop in rotor speed beyond a droop rotor limit speed, the droop protection loop operable to generate a decrease collective command to a collective actuator in response to a measured rotor speed decreasing below a lower droop limit, the droop protection loop operable to generate the decrease in collective command without the detection of an engine failure;

wherein the lower droop limit is below a normal lower rotor speed range; and

wherein the collective actuator is configured 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.

2. The system according to claim 1, wherein a magnitude of the decrease collective command has a nonlinear relationship to an amount of the rotor speed drooping beyond the lower droop limit.

3. The system according to claim 2, wherein the magnitude of the decrease collective command exponentially increases as the amount of the rotor speed drooping beyond the lower droop limit increases.

4. The system according to claim 1, wherein the computer further comprises:

a vertical loop configured to generate a decrease collective command so that the rotorcraft can hold a desired vertical axis state such as vertical speed or vertical altitude.

5. The system according to claim 4, further comprising:

a selector configured to choose the lesser of the decrease collective commands made by the vertical loop and the droop protection loop.

6. The system according to claim 5, further comprising:

a controller configured to receive the decrease collective command and adjust the collective command to minimize an error signal.

7. The system according to claim 6, wherein the controller is a proportional plus integral controller.

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

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

10. An aircraft, comprising:

a rotor blade;

a collective actuator for controlling the pitch of the rotor blade; and

a flight control computer operably associated with the collective actuator, the flight control computer having a droop protection loop operable to generate a decrease collective command to the collective actuator in response to a rotor speed decreasing below a lower droop limit, the droop protection loop operable to generate the decrease in collective command without the detection of an engine failure;

wherein the lower droop limit is below a normal lower rotor speed range; and

wherein the collective actuator is configured to cause a pitch change in the rotor blade as a function of the commanded decrease in collective to provide an initial increase in rotor speed.

11. The aircraft according to claim 10, wherein a magnitude of the decrease collective command has a nonlinear relationship to an amount of the rotor speed drooping beyond the lower droop limit.

12. The aircraft according to claim 11, wherein the magnitude of the decrease collective command exponentially increases as the amount of the rotor speed drooping beyond the lower droop limit increases.

13. The aircraft according to claim 10, wherein the flight control computer further comprises:

a vertical loop configured to generate a decrease collective command so that the rotorcraft can hold a desired vertical axis state such as vertical speed or vertical altitude.

14. The aircraft according to claim 13, further comprising:

a selector configured to choose the lesser of the decrease collective commands made by the vertical loop and the droop protection loop.

15. The aircraft according to claim 14, further comprising:

a controller configured to receive the decrease collective command and adjust the decrease collective command to minimize an error signal.

16. The aircraft according to claim 15, wherein the controller is a proportional plus integral controller.

17. The aircraft according to claim 10, wherein the lower droop limit is a function of a difference between a commanded rotor speed and the rotor speed.