System and method for avoiding inadvertant entry into an unsafe vertical descent speed region for rotorcraft

Patent metadata

Field	Value
Publication number	US-9886039-B2
Application number	US-201514623382-A
Country	US
Kind code	B2
Filing date	Feb 16, 2015
Priority date	Feb 17, 2014
Publication date	Feb 6, 2018
Grant date	Feb 6, 2018

Abstract

A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

First claim

What is claimed is:

1. A flight control system for a rotorcraft, the rotorcraft having a rotor blade and a collective actuator for controlling a pitch of the rotor blade, the flight control system comprising:
a computer having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing only greater amounts of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being selected to prevent a vertical descent speed of the rotorcraft from exceeding a maximum allowable vertical descent threshold at a given forward airspeed.

2. The system according to claim 1 , wherein the first pitch command is made by a pilot.

3. The system according to claim 1 , wherein the first pitch command is made by an autopilot system.

4. The system according to claim 1 , wherein the modified pitch command is operable to impede a movement of a collective stick.

5. The system according to claim 1 , wherein the modified pitch command is operable to impede a movement of a collective stick in a direction that would otherwise decrease collective pitch of the rotor blade.

6. The system according to claim 1 , wherein the vertical descent speed is a predicted vertical descent speed.

7. The system according to claim 1 , wherein the vertical descent speed is a real time vertical descent speed.

8. The system according to claim 1 , wherein the forward airspeed is measured from a sensor.

9. The system according to claim 1 , further comprising: a trim motor associated with a collective stick, the trim motor operable to generate a force that can selectively impede a movement of a collective stick in a direction that would otherwise decrease collective pitch of the rotor blade, the force being a resistant force that can be overcome by a pilot.

10. The system according to claim 1 , the threshold being a plurality of predetermined maximum allowable vertical descent speeds for a plurality of predetermined forward airspeeds.

11. The system according to claim 10 , wherein the predetermined maximum allowable vertical descent speeds increase as the plurality of predetermined forward airspeeds increase.

12. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, the method comprising:
measuring a forward airspeed of the rotorcraft with a sensor;
evaluating a vertical descent of the rotorcraft;
generating a modified collective pitch command in response to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a maximum allowable vertical descent threshold value at the forward airspeed of the rotorcraft, the modified collective pitch command comprising only greater amounts of collective pitch compared to an amount of collective pitch generated by a first pitch command while at the forward airspeed of the rotorcraft.

13. The method according to claim 12 , wherein the sensor is a pitot tube.

14. The method according to claim 12 , wherein the step of evaluating the vertical descent is performed by evaluating data from a second sensor.

15. The method according to claim 12 , further comprising:
impeding a movement of a collective stick in response to the modified collective pitch command.

16. The method according to claim 12 , wherein the first collective pitch command is generated by a pilot.

17. The method according to claim 12 , wherein the first collective pitch command is generated by an autopilot system.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Gillett Luke D
• Schaeffer Joseph M
• Bothwell Christopher M
• Worsham Robert
• Alfred Jillian
• Kim Sung

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C27/16

  Drive of rotors by means, e.g. propellers, mounted on rotor blades · CPC title

• B64C27/10

  arranged coaxially · CPC title

• G05D1/0607 Primary

  specially adapted for aircraft · CPC title