Optical tracking of rotor blade motion

Patent metadata

Field	Value
Publication number	US-9470793-B2
Application number	US-201313766126-A
Country	US
Kind code	B2
Filing date	Feb 13, 2013
Priority date	Feb 13, 2013
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

An optical blade tracking system for a rotary wing aircraft, the system including a light source generating at least one light beam, the light source coupled to a rotor blade of the rotary wing aircraft, wherein movement of the rotor blade is imparted to the light source; a two-dimensional position detector generating signals indicative of a position of the light beam along a first axis and a position of the light beam along a second axis and generating a signal indicative of an angular position of the light beam about a third axis; a processor receiving the signals, the processor determining at least one of lead-lag, flap and pitch of the rotor blade in response to the signals; and a polarizer filter positioned between the light source and the two dimensional position detector, the polarizer filter modulating intensity of the light beam onto the two-dimensional position detector.

First claim

What is claimed is:

1. An optical blade tracking system for a rotary wing aircraft, the system comprising:
a light source generating at least one polarized light beam, the light source coupled to a rotor blade of the rotary wing aircraft, wherein movement of the rotor blade is imparted to the light source;
a two-dimensional position detector generating signals indicative of a position of the light beam along a first axis and a position of the light beam along a second axis, the first axis and the second axis being in the same plane, the two-dimensional position detector generating an intensity signal indicative of an angular position of the light beam about a third axis, the third axis perpendicular to the plane;
a processor receiving the signals, the processor determining at least one of lead-lag, flap and pitch of the rotor blade in response to the signals; and
a polarizer filter positioned between the light source and the two dimensional position detector, the polarizer filter modulating intensity of the light beam onto the two-dimensional position detector.

2. The optical blade tracking system of claim 1 , wherein:
the two-dimensional position detector generates an intensity signal indicative of an intensity of the light beam on the two-dimensional position detector.

3. The optical blade tracking system of claim 2 , wherein:
the intensity signal is indicative of an angular orientation between a light source polarization direction and a polarizer filter polarization direction.

4. The optical blade tracking system of claim 3 , wherein:
the processor determines lead-lag of the rotor blade as:
α≈ c 1 ( V x )

wherein V x is indicative of the position of the light beam along the first axis, and c 1 is a coefficient.

5. The optical blade tracking system of claim 3 , wherein:
the processor determines flap of the rotor blade as:
β≈ c 2 V y

wherein V y is indicative of the position of the light beam along the second axis and c 2 is a coefficient.

6. The optical blade tracking system of claim 3 , wherein:
the processor determines pitch of the rotor blade as:
θ≈ c 3 V IO

wherein V IO is the intensity signal and c 3 is a coefficient.

7. An optical blade tracking system for a rotary wing aircraft, the system comprising:
at least one light source generating a first light beam and a second light beam generated at different times, the light source coupled to a rotor blade of the rotary wing aircraft, wherein movement of the rotor blade is imparted to the light source;
a two-dimensional position detector generating signals indicative of a position of the first light beam and the second light beam along a first axis and along a second axis; and
a processor receiving the signals, the processor determining at least one of lead-lag, flap and pitch of the rotor blade in response to the signals;
wherein the two-dimensional position detector generates signals comprising a first signal indicative of a position of the first light beam along the first axis, a second signal indicative of a position of the first light beam along the second axis, a third signal indicative of a position of the second light beam along the first axis, and a fourth signal indicative of a position of the second light beam along the second axis, the first signal, second signal, third signal and fourth signal indicative of pitch of the rotor blade about a third axis, the third axis perpendicular to the plane.

8. The optical blade tracking system of claim 7 , wherein:
the light source comprises a first light source generating the first light beam and a second light source generating the second light beam.

9. The optical blade tracking system of claim 8 , further comprising:
a switch to alternately provide power the first light source and the second light source.

10. The optical blade tracking system of claim 8 , further comprising:
a shutter to alternately block an output of the first light source and the second light source.

11. The optical blade tracking system of claim 7 , further comprising:
a positionable optical element receiving the light beam and alternately generating the first light beam and the second light beam.

12. The optical blade tracking system of claim 7 , wherein:
the processor determines lead-lag of the rotor blade as:
α≈ c 1 ( V xa +V xb )

wherein V xa is indicative of the position of the first light beam along the first axis, V xb is indicative of the position of the second light beam along the first axis and c 1 is a coefficient.

13. The optical blade tracking system of claim 7 , wherein:
the processor determines flap of the rotor blade as:
β≈ c 2 ( V ya +V yb )

wherein V ya is indicative of the position of the first light beam along the second axis, V yb is indicative of the position of the second light beam along the second axis and c 2 is a coefficient.

14. The optical blade tracking system of claim 7 , wherein:
the processor determines pitch of the rotor blade as:
θ≈ c 3 ( V ya −V yb )/( V xa −V xb )

wherein V ya is indicative of the position of the first light beam along the second axis, V yb is indicative of the position of the second light beam along the second axis, V xa is indicative of the position of the first light beam along the first axis, V xb is indicative of the position of the second light beam along the first axis and c 3 is a coefficient.

15. A method for optical blade tracking for a rotary wing aircraft, the method comprising:
generating a first light beam and a second light beam at different times, a position of the first light beam and a position of the second light beam being responsive to movement of a rotor blade of the rotary wing aircraft;
determining a position of the first light beam along a first axis, a position of the first light beam along a second axis, a position of the second light beam along the first axis, and a position of the second light beam along the second axis, the first axis and the second axis being in the same plane;
determining lead-lag, flap and pitch of the rotor blade in response to the position of the first light beam along the first axis, the position of the first light beam along the second axis, the position of the second light beam along the first axis, and the position of the second light beam along the second axis, wherein the pitch of the rotor blade is about a third axis, the third axis perpendicular to the plane.

16. The method of claim 15 wherein:
determining pitch of the rotor blade includes dividing (i) a difference between the position of the first light beam along the second axis and the position of the second light beam along the second axis by (ii) a difference between the position of the first light beam along the first axis and the position of the second light beam along the first axis.

17. A method for optical blade tracking for a rotary wing aircraft, the method comprising:
generating a polarized light beam, a position of the polarized light beam being responsive to movement of a rotor blade of the rotary wing aircraft;
determining a position of the polarized light beam along a first axis and a position of the polarized light beam along a second axis, the first axis and the second axis being in the same plane;
determining an intensity of the polarized light beam, the intensity of the polarized light beam indicative of an angular position of the polarized light beam about a third axis, the third axis perpendicular to the plane including the first axis and the second axis;
determini

Assignees

• Sikorsky Aircraft Corp

Inventors

• Sun Fanping
• Chaudhry Zaffir A
• Kim Seung Bum
• Fang Austin
• Wasilewski Matthew James
• Lex Robert Mark
• James Curtis S
• Samuels Harvey A
• Guzman Alonso
• Majko David James

Classifications

• G01S17/42 Primary

  Simultaneous measurement of distance and other co-ordinates (indirect measurement G01S17/46) · CPC title

• G01B11/16

  for measuring the deformation in a solid, e.g. optical strain gauge · CPC title

• B64C27/008 Primary

  Rotors tracking or balancing devices · CPC title