Apparatus and methods for aircraft propeller control

Patent metadata

Field	Value
Publication number	US-11292607-B2
Application number	US-201916664122-A
Country	US
Kind code	B2
Filing date	Oct 25, 2019
Priority date	Aug 17, 2016
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

A propeller control system for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A blade angle feedback ring is coupled to the propeller to rotate with the propeller and to move along the longitudinal axis along with adjustment of the blade angle. The feedback ring includes position markers spaced around its circumference. A sensor is positioned adjacent the feedback ring for producing signals indicative of passage of the position markers. A controller is in communication with the sensor, and is configured for: measuring a distance between the position markers, wherein the distance is representative of a longitudinal position of the feedback ring; determining whether a value representative of the longitudinal position is within a first threshold range; and when the value is within the first threshold range, storing the value as a calibration value associated with the blade angle feedback ring.

First claim

What is claimed is:

1. A propeller control system for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle, the control system comprising:
a blade angle feedback ring coupled to the propeller to rotate with the propeller and to move along the longitudinal axis along with adjustment of the blade angle, the blade angle feedback ring comprising a plurality of position markers spaced around its circumference such that a circumferential distance between at least some adjacent ones of the position markers varies along the longitudinal axis;
a sensor positioned adjacent the blade angle feedback ring for producing signals indicative of passage of the position markers, such that an interval between ones of the signals is indicative of a circumferential distance between adjacent ones of the position markers; and
a controller in communication with the sensor and configured for:
measuring a distance between the position markers, wherein the distance is representative of a longitudinal position of the blade angle feedback ring;
determining whether a value representative of the longitudinal position is within a first threshold range; and
when the value is within the first threshold range, storing the value as a calibration value associated with the blade angle feedback ring.

2. The propeller control system of claim 1 , wherein the controller is further configured for:
measuring a subsequent distance between the position markers, wherein the subsequent distance is representative of a subsequent longitudinal position of the blade angle feedback ring;
comparing the subsequent longitudinal position to the calibration value; and
outputting a signal indicative of a propeller blade angle based on the comparing.

3. The propeller control system of claim 1 , wherein the controller is further configured for outputting a calibration status signal indicative of whether the value is within the first threshold range.

4. The propeller control system of claim 1 , wherein the controller is further configured for:
responsive to detecting an engine startup event for an engine associated with the aircraft propeller, measuring a subsequent distance between the position markers, wherein the subsequent distance is representative of a subsequent longitudinal position of the blade angle feedback ring;
determining whether a subsequent value representative of the subsequent longitudinal position is within a second threshold range associated with the calibration value; and
when the subsequent value is outside the second threshold range, producing a warning signal.

5. The propeller control system of claim 4 , the controller being further configured for, prior to producing the warning signal, determining whether a propeller maintenance event occurred prior to the engine startup event.

6. The propeller control system of claim 5 , wherein the warning signal is produced when it is determined that the propeller maintenance event did not occur prior to the engine startup event.

7. The propeller control system of claim 5 , wherein the controller is further configured for updating the calibration value when it is determined that the propeller maintenance event did occur prior to the engine startup event.

8. The propeller control system of claim 4 , wherein the controller is further configured for obtaining a control input from an operator of the propeller control system, wherein the measuring of the subsequent distance between the position markers is performed additionally responsive to obtaining the control input.

9. The propeller control system of claim 4 , wherein the measuring of the subsequent distance is performed when the engine is in a feather condition.

10. The propeller control system of claim 1 , wherein the controller is further configured for producing a warning signal when the value is outside the first threshold range.

11. A method of monitoring an operating condition of an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle, the method comprising:
obtaining, from a sensor, a measurement of a distance between position markers on a blade angle feedback ring mounted for rotation with the propeller and for longitudinal movement along with adjustment of the blade angle, the position markers the position markers spaced around a circumference of the blade angle feedback ring such that a circumferential distance between at least some adjacent ones of the position markers varies along the longitudinal axis, wherein the measured distance is representative of a longitudinal position of the blade angle feedback ring;
determining whether a value representative of the longitudinal position is within a first threshold range; and
when the value is within the first threshold range, storing the value as a calibration value associated with the blade angle feedback ring.

12. The method of claim 11 , further comprising:
obtaining, from the sensor, a subsequent measurement of a subsequent distance between the position markers, wherein the subsequent distance is representative of a subsequent longitudinal position of the blade angle feedback ring;
comparing the subsequent longitudinal position to the calibration value; and
outputting a signal indicative of a propeller blade angle based on the comparing.

13. The method of claim 11 , further comprising outputting a calibration status signal indicative of whether the value is within the first threshold range.

14. The method of claim 11 , further comprising:
responsive to detecting an engine startup event for an engine associated with the aircraft propeller, obtaining, from the sensor, a subsequent measurement of a subsequent distance between the position markers, wherein the subsequent distance is representative of a subsequent longitudinal position of the blade angle feedback ring;
determining whether a subsequent value representative of the subsequent longitudinal position is within a second threshold range associated with the calibration value; and
when the subsequent value is outside the second threshold range, producing a warning signal.

15. The method of claim 14 , further comprising, prior to producing the warning signal, determining whether a propeller maintenance event occurred prior to the engine startup event.

16. The method of claim 15 , wherein the warning signal is produced when it is determined that the propeller maintenance event did not occur prior to the engine startup event.

17. The method of claim 15 , further comprising updating the calibration value when it is determined that the propeller maintenance event did occur prior to the engine startup event.

18. The method of claim 14 , further comprising obtaining a control input from an operator of the propeller control system, wherein the obtaining of the subsequent measurement of the subsequent distance between the position markers is performed additionally responsive to obtaining the control input.

19. The method of claim 14 , wherein the obtaining of the subsequent measurement of the subsequent distance is performed when the engine is in a feather condition.

20. The method of claim 11 , further comprising producing a warning signal when the value is outside the first threshold range.

Assignees

• Pratt & Whitney Canada
• Pratt & Whtney Canada Corp

Inventors

• Yakobov Ella
• Jarvo James Robert

Classifications

• B64D45/0005 Primary

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64D35/02

  specially adapted for specific power plants · CPC title

• B64C11/301 Primary

  characterised by blade position indicating means · CPC title

• B64C11/50

  Phase synchronisation between multiple propellers · CPC title

• B64C11/30

  Blade pitch-changing mechanisms · CPC title