Soft inplane helicopter rotor

• US 4,257,739 A
• Filed: 09/11/1978
• Issued: 03/24/1981
• Est. Priority Date: 09/11/1978
• Status: Expired due to Term

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Textron Inc
• Inventors: Snyder, David E., Covington, Cecil E., Cresap, Wesley L., Sonneborn, Walter G.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/941,255
• Time in Patent Office: 925 Days
• Field of Search: 416/134 A, 416/138 A, 416/140 A, 416/141
• US Class Current: 416/134.00A
• CPC Class Codes: B64C 27/35 having elastomeric joints

Abstract

A helicopter rotor hub assembly (10) in which a blade grip (30) extends inboard of a yoke (14) and transfers centrifugal forces to the yoke (14) through a spherical elastomeric bearing (38). Pitch change of the grip (30) and blade (32) is accommodated by the spherical elastomeric bearing (38) which also acts as the pivot point for lead-lag motion of the blade (32) and grip (30). A lead-lag damper (22) is located inboard of the elastomeric bearing (38) and is connected between one end of the grip (30) spaced away from the lead-lag pivot and the yoke (14) for damping the lead-lag motion between the grip (30) and yoke (14).

Claims

1. In a helicopter blade-yoke coupling, the combination comprising:

a blade grip secured to said blade and extending inboard of the end of said yoke,

an elastomeric retention bearing mounted between said blade grip and said yoke to transfer centrifugal forces from said blade to said yoke while accommodating blade pitch changes and blade lead-lag in a plane about said elastomeric bearing,

a soft inplane, rigid out-of-plane coupling inboard of said elastomeric bearing between one end of said blade grip and said yoke to permit blade lead-lag motion and pitch change while damping movement of said blade grip relative to said yoke, and

a beam-wise flexible plate inboard of said soft inplane coupling and forming part of said yoke to accommodate blade flapping independently of said soft inplane coupling.

2. The combination set forth in claim 1 in which the portion of said yoke extending between said elastomeric bearing and said soft inplane coupling is of a flexible plate character to permit the flexure flapwise of said yoke between said elastomeric bearing and said soft inplane coupling.

3. The combination set forth in claim 1 wherein said soft inplane coupling comprises an elastomeric pad for absorbing lead-lag shear forces between said grip and said yoke.

4. The combination set forth in claim 1 wherein said elastomeric bearing includes a cylindrical elastomeric element for accommodating pitch change of said blade grip and a spherical elastomeric element for carrying the centrifugal force of said blade.

5. In a helicopter rotor, a coupling for joining a blade to a mast while accommodating blade pitch change, lead-lag motion and flapping, the combination comprising,

a flat yoke with an elongate slot therein,

a spindle having a forked outboard end opposite a trunnion at the inboard end with said forked end adapted for rigid connection to said blade, said spindle being dimensioned to fit within the yoke slot with the forked end passing on either side of the outboard end of said yoke,

an elastomeric retention bearing located at the outboard end of said spindle within the yoke slot between said spindle and said yoke to carry the centrifugal loading of said blade and to serve as a pivot for blade lead-lag motion relative to a plane therethrough while permiting pitch change of said spindle and blade relative to said yoke,

an elastomeric damper joining the inboard end of said spindle to said yoke for damping inplane motion of said blade with relatively less stiffness than out-of-plane motion thereof, and

a beam-wise flexible plate inboard of said elastomeric damper and forming part of said yoke to accommodate blade flapping independently of said elastomeric retention bearing.

6. The combination set forth in claim 5 in which the portion of said yoke extending between said elastomeric bearing and said elastomeric damper is of a flexible plate character to permit flexure flapwise of said yoke between said elastomeric bearing and said elastomeric damper.

7. The combination set forth in claim 5 further including a cylindrical elastomeric member disposed about said trunnion and within said elastomeric damper for permitting pitch change of said spindle relative to said yoke.

8. The combination set forth in claim 5 wherein said elastomeric damper comprises a rigid bridge on each side of said yoke extending across said slot in the region of said trunnion with an elastomeric pad bonded between each said bridge and said trunnion for absorbing inplane motion of said spindle as shear forces on said elastomeric pads.

9. The combination set forth in claim 5 wherein said elastomeric bearing comprises

(a) a first load-bearing plate rigidly connected to said spindle and having a spherical surface facing outboard,

(b) a spherical elastomeric element bonded to the spherical surface of said first load-bearing plate,

(c) a compression plate having a spherical surface inboard and a conical surface outboard, the outboard surface of said spherical elastomeric member bonded to the spherical surface of said compression plate,

(d) a conical elastomeric element bonded on the inboard surface thereof to the conical surface of said compression plate, and

(e) a second load-bearing plate rigidly connected to the outboard end of said yoke and having a conical surface inboard bonded to the outboard surface of said conical elastomeric member.

10. Apparatus for coupling a helicopter rotor blade to a yoke mounted on a rotatable mast, comprising:

said yoke including an elongate opening therein;

a blade grip having a bifurcated outboard end secured to the rotor blade and an inboard end disposed within the yoke opening;

retention bearing means connected between the outboard end of said blade grip and said yoke for transferring centrifugal blade loads to said yoke while accommodating blade pitch and lead/lag motion substantially in a plane through said first bearing means; and

bearing/damping means connected between the inboard end of said blade grip and said yoke for accommodating blade pitch and lead/lag motion while damping the lead/lag motion out-of-plane with relatively greater stiffness than the in-plane motion;

said yoke being adapted with a predetermined flexure zone adjacent said second bearing means for accommodating blade flap independently of said first and second bearing means.

11. The apparatus of claim 10, wherein said retention bearing means comprises:

a first rigid plate secured to said blade grip and having a substantially spherical surface facing outboard;

a second rigid plate secured to said yoke and having a substantially conical surface facing inboard;

a first elastomeric element with substantially spherical surfaces bonded to said first plate;

a second elastomeric element with substantially conical surfaces bonded to said second plate; and

a rigid insert with mating surfaces bonded between said first and second elastomeric elements.

12. The apparatus of claim 10, wherein said bearing/damping means comprises:

an annular elastomeric bearing including a housing bonded to elastomeric and rigid elements bonded to said blade grip;

a pair of bridge members transverse to said blade grip and secured to said yoke;

elastomeric shear pads bonded between said bridge members and the housing of said annular bearing; and

stop means for limiting in-plane lead/lag motion of said blade grip.

13. The apparatus of claim 10, wherein the inboard end of said blade grip is of substantially circular cross-section tapering from the outboard end to the inboard end.

14. In an apparatus for coupling a rotor blade to a yoke on a rotatable mast of the type wherein the yoke includes an elongate opening and is adapted to flex flapwise thereby accommodating blade flapping, the improvement comprising:

a blade grip having a bifurcated outboard end secured to the rotor blade and an inboard end disposed within the yoke opening;

the inboard end of said blade grip being tapered;

first elastomeric bearing means connected between the outboard end of said blade grip and said yoke for transferring centrifugal blade loads to said yoke while accommodating blade pitch about a control axis extending through said blade grip and blade lead/lag motion relative to a plane extending through said first bearing means;

second elastomeric bearing means connected between the inboard end of said blade grip and said yoke for accommodating blade pitch and lead/lag; and

means connected between said second elastomeric bearing means and yoke for damping in-plane blade lead/lag in shear and for damping out-of-plane lead/lag in compression.