Variable lower limit collective governor to improve recovery

Patent metadata

Field	Value
Publication number	US-9352831-B2
Application number	US-201313889454-A
Country	US
Kind code	B2
Filing date	May 8, 2013
Priority date	May 8, 2013
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade, and a limiter configured to selectively remove the threshold limit of the governor when the collective pitch control exceeds a threshold limit, so as to permit a pilot full command of the collective above the threshold limit. The threshold limit is selectively removed and phased back in to provide temporary pilot control to “cushion” landing of an aircraft when an engine has failed.

First claim

What is claimed is:

1. A control system for an aircraft, comprising:
a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade; the governor having a threshold limit relating to the maximum pitch angle of the rotor blade; and
a limiter configured to selectively remove the threshold limit, so as to permit a pilot full command of the collective above the threshold limit;
wherein command signals from the governor and command signals from the limiter are summed to generate a total symmetric collective pitch command for controlling the pitch of the rotor blade.

2. The control system of claim 1 , wherein the limiter is configured to be selectively activated and deactivated.

3. The control system of claim 2 , further comprising:
a first engine and a second engine;
wherein the limiter is deactivated while each engine is operational.

4. The control system of claim 3 , wherein the limiter is configured to generate a baseline lower limit when deactivated.

5. The control system of claim 2 , wherein the limiter is activated upon the failure of an engine and when the collective is increased above the threshold limit.

6. The control system of claim 1 , wherein the command signals from the limiter are based upon the command signals from the governor, the governor configured to selectively communicate with the limiter.

7. The control system of claim 1 , wherein the command signals from the limiter are configured to adjust in relation to the collective position, so as to remove the threshold of the governor.

8. The control system of claim 1 , wherein the limiter is configured to remove the threshold limit for a selected time limit, the threshold limit being phased back into operation upon expiration of the time limit.

9. A rotorcraft comprising:
a first engine and a second engine;
a rotor and rotor blades individually operable with first engine and the second engine; and
a flight control system configured to regulate the speed of the rotor through collective pitch control of the rotor blades, the flight control system selectively removing a threshold limit relating to the maximum pitch angle of the rotor blades, so as to permit a pilot full command of the collective during operations in which the first engine is inoperative;
wherein the threshold limit is removed for a selected time limit, the threshold limit being phased back into operation upon expiration of the time limit.

10. The rotorcraft of claim 9 , wherein the threshold limit is removed when the first engine is inoperative and the maximum pitch angle desired by the pilot exceeds the threshold limit.

11. The rotorcraft of claim 9 , wherein the flight control system monitors the speed of the rotors and the operability of the first engine and the second engine.

12. The rotorcraft of claim 9 , wherein the first engine is coupled to a first nacelle and the second engine is coupled to a second nacelle, the flight control system adjusts the pitch angle of the rotors as a result of a nacelle schedule as measured by a nacelle angle sensor.

13. A method of improving an arrest rate of descent at touchdown of an aircraft, comprising:
determining the operational status of a first engine and a second engine;
comparing a desired collective pitch angle to that of a threshold limit of a governor; and
generating a limiting value configured to remove the threshold limit as the desired collective pitch angle exceeds the threshold limit and as the first engine is inoperative;
wherein removal of the threshold limit provides a pilot with full command of the collective pitch angle to slow the rate of descent of the aircraft at touchdown; and
wherein the limiting value is summed with command signals within the governor to lower the threshold limit.

14. The method of claim 13 , wherein the threshold limit is removed temporarily for a period of time.

15. The method of claim 13 , wherein the limiting value is dependent upon the collective pitch angle.

16. The method of claim 13 , further comprising:
reinstating the threshold limit upon when the first engine and second engine are operative.

17. The method of claim 13 , wherein removal of the threshold limit is automatically performed by a flight control system.

Assignees

• Schaeffer Joseph M
• Bell Helicopter Textron Inc

Inventors

• Schaeffer Joseph M

Classifications

• B64C27/57 Primary

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