Rotorcraft and associated rotor blade position monitoring system and method

Patent metadata

Field	Value
Publication number	US-10287007-B2
Application number	US-201615000179-A
Country	US
Kind code	B2
Filing date	Jan 19, 2016
Priority date	Jan 19, 2016
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

A rotorcraft including a rotor hub, a pitch housing moveable relative to the rotor hub about at least a feather axis and a flap axis, the pitch housing defining an internal volume, a bearing pin, the inboard end portion of the bearing pin being fixedly connected to the rotor hub, wherein the bearing pin defines the feather axis, a spherical bearing connected to the inboard end portion of the pitch housing and defining the flap axis, wherein the bearing pin extends through the spherical bearing, a rotor blade connected to the outboard end portion of the pitch housing, and a sensor assembly positioned in the internal volume and operatively connected to both the pitch housing and the outboard end portion of the bearing pin.

First claim

What is claimed is:

1. A rotorcraft comprising:
a rotor hub;
a pitch housing connected to said rotor hub and moveable relative to said rotor hub about at least a feather axis and a flap axis, said pitch housing defining an internal volume and comprising an inboard end portion and an outboard end portion;
a bearing pin comprising an inboard end portion and an outboard end portion, said inboard end portion of said bearing pin being fixedly connected to said rotor hub, wherein said bearing pin defines said feather axis;
a spherical bearing connected to said inboard end portion of said pitch housing and defining said flap axis, wherein said bearing pin extends through said spherical bearing;
a rotor blade connected to said outboard end portion of said pitch housing; and
a sensor assembly positioned, at least partially, in said internal volume and operatively connected to both said pitch housing and said outboard end portion of said bearing pin, said sensor assembly comprising:
a first position sensor configured to sense angular displacement of said pitch housing relative to said rotor hub about said flap axis; and
a second position sensor configured to sense angular displacement of said pitch housing relative to said rotor hub about said feather axis.

2. The rotorcraft of claim 1 further comprising a mast, wherein said rotor hub is connected to said mast.

3. The rotorcraft of claim 1 further comprising a strap pack connecting said rotor blade to said rotor hub, wherein a portion of said strap pack is received in said internal volume.

4. The rotorcraft of claim 1 further comprising a bearing housing assembly connected to said inboard end portion of said pitch housing, wherein said bearing housing assembly defines a bore and said spherical bearing is received in said bore.

5. The rotorcraft of claim 1 wherein said spherical bearing comprising a spherical member and a socket member, said spherical member defining a bore, and wherein said bearing pin is connected to said spherical member and extends through said bore defined by said spherical member.

6. The rotorcraft of claim 1 wherein at least one of said first position sensor and said second position sensor comprises a potentiometer.

7. The rotorcraft of claim 1 wherein said sensor assembly further comprises a first lever member pivotally connected to said first position sensor about a first axis of rotation.

8. The rotorcraft of claim 7 wherein said first lever member pivots about said first axis of rotation in response to angular displacement of said pitch housing relative to said rotor hub about said flap axis.

9. The rotorcraft of claim 7 wherein said first axis of rotation is substantially parallel with said flap axis.

10. The rotorcraft of claim 7 wherein said sensor assembly further comprises a second lever member pivotally connected to said second position sensor about a second axis of rotation.

11. The rotorcraft of claim 10 wherein an angle between said second axis of rotation and said feather axis ranges from 0 degrees to at most 25 degrees.

12. The rotorcraft of claim 10 wherein said second lever member pivots about said second axis of rotation in response to angular displacement of said pitch housing relative to said rotor hub about said feather axis.

13. The rotorcraft of claim 10 wherein said second lever member comprises a first end portion and an opposed second end portion, wherein said first end portion is pivotally connected to said second position sensor about said second axis of rotation, and wherein said second end portion is operatively connected to said first lever member.

14. The rotorcraft of claim 13 wherein said operative connection between said second end portion of said second lever member and said first lever member comprises a link member and a second spherical bearing, and wherein said second spherical bearing is disposed between said link member and said first lever member.

15. The rotorcraft of claim 10 wherein said sensor assembly further comprises a support member connected to said pitch housing by way of a tie member, wherein said second position sensor is mounted on said support member.

16. The rotorcraft of claim 15 wherein said tie member is hingedly connected to said support member.

17. The rotorcraft of claim 16 wherein said support member is connected to said bearing pin by way of said first lever member.

18. The rotorcraft of claim 17 further comprising a spherical bearing disposed between said first lever member and said support member.

19. The rotorcraft of claim 1 wherein said first position sensor is fixedly connected to said outboard end portion of said bearing pin.

20. A rotorcraft comprising:
a rotor hub;
a pitch housing connected to said rotor hub and moveable relative to said rotor hub about at least a feather axis and a flap axis, said pitch housing defining an internal volume and comprising an inboard end portion and an outboard end portion;
a bearing pin comprising an inboard end portion and an outboard end portion, said inboard end portion of said bearing pin being fixedly connected to said rotor hub, wherein said bearing pin defines said feather axis;
a spherical bearing connected to said inboard end portion of said pitch housing and defining said flap axis, wherein said bearing pin extends through said spherical bearing such that said outboard end portion of said bearing pin protrudes from said spherical bearing toward said internal volume;
a rotor blade connected to said outboard end portion of said pitch housing; and
a sensor assembly positioned, at least partially, in said internal volume and operatively connected to both said pitch housing and said outboard end portion of said bearing pin, said sensor assembly comprising:
a first potentiometer;
a first lever member pivotally connected to said first potentiometer about a first axis of rotation, wherein said first lever member pivots about said first axis of rotation in response to angular displacement of said pitch housing relative to said rotor hub about said flap axis;
a second potentiometer; and
a second lever member pivotally connected to said second potentiometer about a second axis of rotation, wherein said second lever member pivots about said second axis of rotation in response to angular displacement of said pitch housing relative to said rotor hub about said feather axis.

Assignees

• Boeing Co

Inventors

• Thomas Jeffrey M
• Alderete David
• Costello Richard

Classifications

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C27/008

  Rotors tracking or balancing devices · CPC title

• B64C27/78

  in association with pitch adjustment of blades of anti-torque rotor · CPC title

• B64C27/39 Primary

  with individually articulated blades, i.e. with flapping or drag hinges · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title