Emergency collective actuator and method for a helicopter

Patent metadata

Field	Value
Publication number	US-10099781-B2
Application number	US-201715723594-A
Country	US
Kind code	B2
Filing date	Oct 3, 2017
Priority date	Nov 24, 2009
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.

First claim

What is claimed is:

1. For use with a helicopter including a rotor system having a main rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control, an apparatus comprising:
an actuator arrangement that is configured to change the adjustable pitch by exerting an actuation force responsive to a motor rotating a motor output shaft in a given direction to bias the adjustable pitch toward a minimum collective pitch position and the pilot is able to overcome said actuation force by applying a counterforce to the collective control to cause the motor shaft to rotate in a reverse direction; and
a control arrangement that is configured to receive a signal that is indicative of a low rotor RPM condition and to respond to said signal by activating the actuator arrangement to exert the actuation force at least for a predetermined period of time.

2. The apparatus of claim 1 wherein said control arrangement is further configured for entering a lockout interval immediately following said predetermined period of time during which lockout interval the Low RPM signal is disabled from activating the actuator arrangement.

3. The apparatus of claim 1 wherein said predetermined period of time is in a range from 1 second to 10 seconds.

4. The apparatus of claim 1 configured to apply said force within 1 millisecond of receiving the signal.

5. The apparatus of claim 1 wherein said collective control includes an arm that is pivotable to change the adjustable pitch of the rotor and said arm includes an arm length extending from a pivot end to a distal end and wherein said actuator arrangement is connected to an intermediate position along the arm length to apply said force.

6. The apparatus of claim 5 positioned below said collective control such that said force pulls on said collective control from said intermediate position.

7. The apparatus of claim 6 wherein said actuator arrangement includes a cable having one end that is attached to the intermediate position of the arm length for pulling on the collective control.

8. The apparatus of claim 7 wherein the actuator arrangement includes an electric motor for applying said force to the cable by rotating in the given direction.

9. The apparatus of claim 8 wherein motor output shaft supports a drum having one or more windings of the cable wound around the drum.

10. The apparatus of claim 9 wherein said drum is supported for co-rotation with said motor shaft and wherein said cable extends around said drum from said windings to an opposing end of the cable that is attached to a spring that is supported for maintaining a tension continuously on the cable to take up any slack in the cable.

11. The apparatus of claim 10 wherein said spring is a coil spring having a first end that is attached to the opposing end of the cable and a second end that is fixedly attached to the helicopter.

12. The apparatus of claim 1 wherein said control arrangement includes a pilot actuatable switch that is switchable by the pilot to selectively disable the application of said force to the collective.

13. The apparatus of claim 1 wherein said control arrangement includes an arrangement for using at least a detected altitude of the helicopter above a surface of the ground to disable the application of said force below a predetermined altitude.

14. The apparatus of claim 1 wherein said control arrangement is configured for disabling the application of said force based on a detected altitude of the helicopter in combination with a detected airspeed of the helicopter.

15. The apparatus of claim 1 wherein said control arrangement is configured for disabling the application of said force within at least one predetermined unsafe region of a height-velocity diagram for the helicopter.

16. The apparatus of claim 1 wherein said control arrangement includes a comparator which compares the engine RPM to an engine RPM threshold during the predetermined period of time to respond to the low RPM engine condition.

17. The apparatus of claim 1 wherein the control arrangement is configured to turn off the motor responsive to an inactive state of the low rotor RPM engine condition during the predetermined period of time.

18. The apparatus of claim 1 wherein the control arrangement is configured to monitor the engine RPM in a continuous loop and to initiate the predetermined period of time responsive to detecting the low RPM engine condition.

19. The apparatus of claim 18 wherein the control arrangement, responsive to detecting the low RPM engine condition, is further configured to thereafter reconfirm the low RPM engine condition before causing the actuator arrangement to exert the actuation force.

20. The apparatus of claim 1 wherein said control arrangement is further configured for entering a lockout interval immediately following said predetermined period of time during which lockout interval the low RPM engine condition is disabled from activating the actuator arrangement.

Assignees

• Merlin Technology Inc

Inventors

• Mercer John E
• Marvin Mark H

Classifications

• B64C27/006

  Safety devices · CPC title

• B64C27/59

  mechanical · CPC title

• B64C27/57 Primary

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

• B64C27/04

  Helicopters · CPC title