Torque and thrust control of a propeller

Patent metadata

Field	Value
Publication number	US-10336436-B2
Application number	US-201515329411-A
Country	US
Kind code	B2
Filing date	Sep 28, 2015
Priority date	Sep 30, 2014
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

A method for controlling a propeller of an aircraft, comprises receiving, with a processor, one or more signals indicative of commanded collective pitch of the propeller; receiving, with the processor, one or more sensed signals indicative of propeller axial speed, propeller rotational speed, and air density; estimating, with the processor, a propeller torque and propeller thrust from one or more of the propeller axial speed, the propeller rotational speed, and the air density; determining, with the processor, information indicative of an error value between a desired torque and a measured torque in the propeller; determining, with the processor, information indicative of a corrected pitch command in response to the determining of the error value; combining, with the processor, the corrected pitch command with the propeller rotational speed into an adjustment solution; providing, with the processor, the propeller with the adjustment solution.

First claim

What is claimed is:

1. A method for controlling a propeller of an aircraft, comprising:
receiving, with a processor, one or more signals indicative of commanded collective pitch of the propeller associated with a desired torque;
receiving, with the processor, one or more sensed signals from at least one sensor mounted to the aircraft, one or more sensed signals being indicative of propeller axial speed, propeller rotational speed, and air density;
estimating, with the processor, a propeller torque and propeller thrust from one or more of the propeller axial speed, the propeller rotational speed, and the air density;
determining, with the processor, information indicative of an error value between a desired torque and a measured torque in the propeller;
determining, with the processor, information indicative of a corrected pitch command in response to the determining of the error value;
combining, with the processor, the corrected pitch command with the propeller rotational speed into an adjustment solution, the propeller rotational speed being governed by a full authority engine controller;
providing, with the processor, the propeller with the adjustment solution, wherein providing the propeller with the adjustment solution includes changing an attitude of one or more propeller blades of the propeller while maintaining a constant rotational speed of the propeller;
receiving, with the processor, a subsequent error value between the desired torque and the measured torque in response to the providing of the adjustment solution.

2. The method of claim 1 , further comprising determining an estimated upper limit of a collective pitch as a function of maximum torque and maximum thrust from a predefined schedule.

3. The method of claim 2 , further comprising determining an estimated lower limit for the collective pitch as a function of minimum torque and minimum thrust from a predefined schedule.

4. The method of claim 3 , further comprising determining each of an upper limit collective pitch command and a lower limit collective pitch command from the estimated upper and lower limits.

5. The method of claim 1 , further comprising adjusting the corrected pitch command as a function of at least one of the commanded collective pitch, the propeller axial speed, and the propeller rotational speed.

6. The method of claim 1 , further comprising determining a pitch rate from the commanded collective pitch, the estimated torque, and the estimated thrust.

7. The method of claim 6 , further comprising applying each of a lower limit constant value and pitch rate limiting value to the commanded collective pitch to drive down the commanded collective pitch to the lower limit constant value, the lower limit constant value representing a lower limit of a collective pitch.

8. The method of claim 7 , further comprising applying the lower limit constant value if at least one of the propeller thrust or the propeller torque is greater than its respective upper limit value.

9. The method of claim 6 , further comprising applying each of an upper limit constant value and pitch rate limiting value to the commanded collective pitch to drive up the commanded collective pitch to the upper limit constant value, the upper limit constant value representing an upper limit of a collective pitch.

10. The method of claim 9 , further comprising applying the upper limit constant value if at least one of the propeller thrust or the propeller torque is lesser than its respective lower limit value.

11. A system for controlling a plurality of propeller blades of an aircraft, comprising
a propeller comprising the plurality of blades, wherein the propeller is associated with a sensor;
a processor; and
memory having instructions stored thereon that, when executed by the processor, cause the system to:
receiving one or more signals indicative of commanded collective pitch of the propeller associated with a desired torque;
receive one or more sensed signals indicative of propeller axial speed, propeller rotational speed, and air density;
determine information indicative of an error value between the desired torque and a measured torque in the propeller;
determine information indicative of a corrected pitch command in response to the determining of the error value;
combine the corrected pitch command with the propeller rotational speed into an adjustment solution, the propeller rotational speed being governed by a full authority engine controller;
provide the propeller with the adjustment solution, wherein providing the propeller with the adjustment solution includes changing an attitude of one or more of the plurality of blades while maintaining a constant rotational speed of the propeller; and
receive a subsequent error value between the desired torque and the measured torque in response to the providing of the adjustment solution.

12. The system of claim 11 , wherein the processor is configured to determine an estimated upper limit of a collective pitch as a function of maximum torque and maximum thrust from a predefined schedule.

13. The system of claim 12 , wherein the processor is configured to determine an estimated lower limit for the collective pitch as a function of minimum torque and minimum thrust from a predefined schedule.

14. The system of claim 13 , wherein the processor is configured to determine each of an upper limit collective pitch command and a lower limit collective pitch command from the estimated upper and lower limits.

15. The system of claim 11 , wherein the processor is configured to adjust the corrected pitch command as a function of at least one of the commanded collective pitch, the propeller axial speed, and the propeller rotational speed.

16. The system of claim 11 , wherein the processor is configured to estimate a torque and thrust from one or more of the propeller axial speed, the propeller rotational speed, and the air density.

17. The system of claim 11 , wherein the processor is configured to determine a pitch rate from the commanded collective pitch, the estimated torque, and the estimated thrust, and apply each of a lower limit constant value and a pitch rate limiting value to the commanded collective pitch to drive down the commanded collective pitch to the lower limit constant value, the lower limit constant value representing a lower limit of a collective pitch.

18. The system of claim 17 , wherein the processor is configured to apply the lower limit constant value if at least one of the propeller thrust or the propeller torque is greater than its respective upper limit value.

19. The system of claim 11 , wherein the processor is configured to determine a pitch rate from the commanded collective pitch, the estimated torque, and the estimated thrust, and apply each of an upper limit constant value and pitch rate limiting value to the commanded collective pitch to drive up the commanded collective pitch to the upper limit constant value, the upper limit constant value representing an upper limit of a collective pitch.

20. The system of claim 19 , wherein the processor is configured to apply the upper limit constant value if at least one of the propeller thrust or the propeller torque is lesser than its respective lower limit value.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Siu Sunny K
• Fegely Cody
• Wittmer Kenneth S
• Knag John
• Greenfield Aaron L

Classifications

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C2027/8272

  comprising fins, or movable rudders · CPC title

• B64C11/44 Primary

  electric · CPC title

• B64C2027/8236

  including pusher propellers · CPC title

• B64C2027/8281

  comprising horizontal tail planes · CPC title