Multi-piece inboard-beam

Patent metadata

Field	Value
Publication number	US-10450059-B2
Application number	US-201815882573-A
Country	US
Kind code	B2
Filing date	Jan 29, 2018
Priority date	Jan 29, 2018
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.

First claim

What is claimed is:

1. An inboard bearing assembly for a rotorcraft, comprising:
an inboard beam including a post;
a beam fitting, including an outer plate aligned with an inner plate, engaged with the post;
the beam fitting connected to the inboard beam at an anti-rotational connection, where the inboard beam is prevented from rotation around a central longitudinal axis of the inboard beam relative to the beam fitting; and
the beam fitting connected to a composite grip between the outer plate and the inner plate, where the post is positioned in a slot formed in the grip.

2. The inboard bearing assembly of claim 1 , further comprising a shaft extending from the inboard beam opposite a curved surface in the inboard beam.

3. The inboard bearing assembly of claim 2 , further comprising:
a spindle bearing attached to the shaft; and
a centrifugal force (“CF”) bearing held by the curved surface.

4. The inboard bearing assembly of claim 3 , wherein a CF load path is through the composite grip to the beam fitting to the inboard beam to the CF bearing.

5. The inboard bearing assembly of claim 1 , further comprising:
a flange connected between the inboard beam and the post; and
the anti-rotational connection comprises the inner plate connected to the flange at a plurality of points.

6. The inboard bearing assembly of claim 1 , wherein:
the post is a first anti-rotation post;
a second anti-rotation post extends from the inboard beam;
the beam fitting includes a first anti-rotation aperture and a second anti-rotation aperture; and
wherein the anti-rotational connection includes the first anti-rotation post engaged with the first anti-rotation aperture and the second anti-rotation post engaged with the second anti-rotation aperture.

7. The inboard bearing assembly of claim 1 , wherein the anti-rotational connection comprises a non-circular portion of the post secured in a non-circular aperture of the beam fitting.

8. The inboard bearing assembly of claim 7 , wherein:
the post includes a threaded section; and
a locking ring threadably engaged with the threaded section.

9. A rotor blade assembly of a rotorcraft, comprising:
a metal yoke including a central aperture;
a drive shaft connected to the metal yoke at the central aperture;
a metal yoke arm, formed by the metal yoke, extending radially from the central aperture;
a beam fitting connected to an inboard beam at an anti-rotational connection;
a post extending from the inboard beam;
a centrifugal force (“CF”) bearing held by the metal yoke arm and the inboard beam;
a grip connected to the beam fitting at a double shear connection, wherein the post is positioned in a slot formed in the grip; and
a CF load path of the rotor blade assembly through the grip, the beam fitting, the inboard beam, the CF bearing, the metal yoke.

10. The rotor blade assembly of claim 9 , wherein:
the beam fitting comprises an outer plate aligned with an inner plate defining a space between the outer plate and the inner plate; and
the double shear connection comprises the grip positioned in the space and connected to the outer plate and the inner plate.

11. The rotor blade assembly of claim 9 , further comprising:
a shaft extending from the inboard beam opposite a curved surface in the inboard beam;
a spindle bearing attached to the shaft; and
the CF bearing held by the curved surface.

12. The rotor blade assembly of claim 9 , further comprising a flange connected between the inboard beam and the beam fitting, where the anti-rotational connection connects the beam fitting to the flange at a plurality of points.

13. The rotor blade assembly of claim 9 , further comprising:
a second anti-rotation post extending from the inboard beam;
a first anti-rotation aperture in the beam fitting;
a second anti-rotation aperture in the beam fitting; and
wherein the anti-rotational connection comprises the post engaged with the first anti-rotation aperture and the second anti-rotation post engaged with the second anti-rotation aperture.

14. The rotor blade assembly of claim 9 ,
wherein the anti-rotational connection comprises a non-circular portion of the post secured in a non-circular aperture of the beam fitting.

15. The rotor blade assembly of claim 9 , further comprising:
the post extending from the inboard beam through an aperture in the beam fitting;
a threaded section formed in the post; and
a locking ring threadably engaged with the threaded section and engaged with the beam fitting.

16. The rotor blade assembly of claim 9 , wherein the beam fitting further comprises:
an outer plate aligned with an inner plate;
a cylindrical hub connecting the outer plate to the inner plate; and
the outer plate connected to the grip and the inner plate connected to the grip, where the grip is positioned between the outer plate and the inner plate.

17. An inboard bearing assembly for a rotorcraft, comprising:
an inboard beam;
a post extending from the inboard beam;
a beam fitting, including an outer plate aligned with an inner plate, engaged with the post;
the beam fitting connected to the inboard beam at an anti-rotational connection, where the inboard beam is prevented from rotation around a central longitudinal axis of the inboard beam relative to the beam fitting;
the beam fitting connected to a grip between the outer plate and the inner plate, where the post is positioned in a slot formed in the grip;
a shaft extending from the inboard beam opposite a curved surface in the inboard beam;
a spindle bearing attached to the shaft;
a centrifugal force (“CF”) bearing held by the curved surface; and
a CF load path through the grip, the beam fitting, the inboard beam, and the CF bearing.

18. The inboard bearing assembly of claim 17 , further comprising:
a flange connected to the inboard beam and the post; and
the anti-rotational connection comprises the beam fitting connected to the flange at a plurality of points.

19. The inboard bearing assembly of claim 17 , further comprising:
a second post extending from the inboard beam;
a first anti-rotational aperture formed in the beam fitting;
a second anti-rotational aperture formed in the beam fitting; and
the anti-rotational connection comprises the post engaged with the first anti-rotational aperture and the second post engaged with the second anti-rotational aperture.

20. The inboard bearing assembly of claim 17 , wherein the anti-rotational connection comprises a non-circular portion of the post non-rotationally secured in a non-circular aperture of the beam fitting.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Cravener Kyle Thomas
• Baldwin Tyler Wayne
• Torske Nicholas Allen

Classifications

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title

• B64C27/33 Primary

  having flexing arms · CPC title

• B64C27/22

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title