WO2004094859A2 - Snubber - Google Patents
Snubber Download PDFInfo
- Publication number
- WO2004094859A2 WO2004094859A2 PCT/US2004/011754 US2004011754W WO2004094859A2 WO 2004094859 A2 WO2004094859 A2 WO 2004094859A2 US 2004011754 W US2004011754 W US 2004011754W WO 2004094859 A2 WO2004094859 A2 WO 2004094859A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- snubber
- inner member
- retainer
- shim
- spacer stack
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F3/00—Spring units consisting of several springs, e.g. for obtaining a desired spring characteristic
- F16F3/08—Spring units consisting of several springs, e.g. for obtaining a desired spring characteristic with springs made of a material having high internal friction, e.g. rubber
- F16F3/087—Units comprising several springs made of plastics or the like material
- F16F3/0873—Units comprising several springs made of plastics or the like material of the same material or the material not being specified
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/35—Rotors having elastomeric joints
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F1/00—Springs
- F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
- F16F1/40—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers consisting of a stack of similar elements separated by non-elastic intermediate layers
Definitions
- This invention relates to elastomeric bearings, and more particularly to elastomeric bearings used in helicopter main rotor and tail rotor assemblies.
- Exemplary snubber/damper units are shown in U.S. patents 5,188,513, 5,092,738, 4,244,677, and 4,105,266.
- An exemplary snubber/damper is used in a bearingless rotor application to accommodate relative movement and orientation changes of an inner blade member to an outer blade or mounting member.
- two snubber/damper subunits are mounted on opposite sides of the inner member.
- the subunits include a spherical stack of bonded metallic shims and elastomeric spacers to accommodate pitch and flap motions and a flat stack to accommodate lead-lag and, if present, longitudinal motions.
- the spherical stack is commonly identified as the snubber and the flat stack is commonly identified as the damper.
- the spherical layers of the two subunits are concentric.
- one aspect of the invention involves a snubber system for permitting relative rotation of a first member and a second member.
- a snubber inner member has a doubly convex outer surface portion having a central longitudinal axis.
- a shim/spacer stack secured to the outer surface portion couples the snubber inner member to the second member.
- a retainer having one or more engagement surfaces cooperates with one or more engagement surfaces of the snubber inner member to constrain lateral movement of the snubber inner member relative to the retainer while permitting longitudinal movement of the snubber inner member away from the retainer.
- An elastomer secures the retainer to the first member.
- the shim/spacer stack may be outwardly doubly convex and the snubber system may further have a flat shim/spacer stack coupling the outwardly doubly convex shim/spacer stack to the second member.
- the snubber system may include a second such inner member, shim/spacer stack, retainer, and elastomer, opposite the first.
- the shim/spacer stack may consist essentially of a number of metallic shims and a number of elastomeric spacers secured to each other as a unit.
- the snubber inner member may have a flange extending radially outward beyond an inboard portion of the doubly convex outer surface portion.
- the snubber inner member one or more engagement surfaces may comprise a perimeter portion of a socket and the retainer one or more engagement surfaces may comprise an outwardly projecting projection.
- FIG. 1 is a sectional view of a snubber/damper in a neutral condition.
- FIG. 2 is a sectional view of an alternate snubber/damper in a neutral condition.
- FIG. 3 is a sectional view of the snubber/damper of FIG. 1 in a pitched condition.
- Like reference numbers and designations in the various drawings indicate like elements.
- FIG. 1 shows a snubber/damper system 20 which couples an inner member 22 to an outer member 24.
- the inner member 22 is a root portion of a helicopter rotor blade flexbeam.
- the exemplary outer member 24 is a torque tube portion of the blade extending outward and secured to a distal portion of the flexbeam (e.g., via bolts).
- the exemplary inner member 22 has an elongate cross-section transverse to its central longitudinal axis 500.
- the inner member 22 and this cross-section have a top 26A and a bottom 26B and relatively shorter sides 28A and 28B.
- the snubber/damper system 20 holds the inner member 22 in a neutral orientation relative to the outer member 24 wherein the central top/bottom surface normal 502 of the flexbeam is pitched at an angle ⁇ o relative to an axis 504 of the snubber/damper system.
- the exemplary snubber/damper system 20 includes similar components above and below the inner member 22.
- the core of the upper and lower halves of the snubber/damper system is a respective upper and lower snubber inner member 30 A, 30B.
- Each inner member is coupled to the associated top or bottom surface by a retainer 32A, 32B and pad 34A, 34B (both described in further detail below).
- Each inner member 30A, 30B has an outboard spherical surface portion 36A, 36B.
- the respective spherical surface portions 36A, 36B have centers of curvature 506A and 506B which, in the neutral condition, fall along the axis 504 spaced outward from its intersection with the flexbeam central axis 500.
- a shim/spacer stack 40A, 40B is secured to each inner member 30A, 30B.
- Each stack 40A, 40B has alternating elastomeric spacers 42 and metal shims 44 secured to each other.
- the spacers and shims each have inboard and outboard surfaces with centers of curvature at the associated center 506A, 506B.
- the exemplary spacers and shims are annular, leaving each stack 40A, 40B with a central cavity 46 provided by the shim/spacer central apertures.
- the outboard surface of each stack is secured to an inboard surface 50A, 50B of a metallic adapter or transition shim 52A,
- the surfaces 50A, 50B are concentric with their respective shim stacks and inner member outer surfaces.
- the adaptors 52A, 52B each have a flat outer surface 54A, 54B.
- An outer (damper) shim/spacer stack 56 A, 56B has spacers 57 and shims 58.
- Each stack 56 A, 56B has an inboard surface secured to the outer surface 54A, 54B and an outboard surface secured to a plate 60 A, 60B.
- Each plate 60 A, 60B is captured within an associated cap 62 A,
- the elastome ⁇ c pads 34A and 34B provide strain isolation between the inner member 22 and the retainers 32A and 32B. Accordingly, the pads may advantageously be relatively thick.
- An exemplary uncompressed pad thickness is 0.025 inch.
- An exemplary range of uncompressed thicknesses is 0.010-0.040 inch, more narrowly, 0.015-0.035 inch.
- An exemplary pad mate ⁇ al is natural rubber (e.g., per ASTM D 2000).
- An exemplary retainer matenal is chopped glass fiber in resm (e.g., per MIL-M-46069) and an exemplary retainer thickness is 0.065 inch.
- the exemplary snubber inner members have central depending projections 70 and outboard radially-extending flanges 72. The projections 70 are received within apertures 74 and 76 in the associated retainer and pad, respectively.
- the flanges 72 serve to provide angular stability to the snubber inner members. In an exemplary embodiment, the flanges 72 are not captured beneath a retainer clip.
- FIG. 2 shows an alternate inner member mounting configuration in which the cooperating mterengaged mounting features of the inner member and retainer are reversed from those of FIG. 1.
- each inner member 130A, 130B has a socket 174 extending toward the surface 136A, 136B from the underside of the inner member.
- a complementary projection 170 extends from the outboard surface of the associated retainer 132A, 132B.
- the retainer may advantageously be metallic (e.g., Al or Ti alloys).
- each pad 134A, 134B lacks the central aperture of the FIG. 1 pads.
- the projection 170 and socket 174 are largely nght circular cylinders.
- the projection 170 has a p ⁇ ncipal radius and a flat distal end surface 175 a given height above the remaining outboard surface of the retainer.
- the socket has a principal diameter slightly greater than the local projection diameter to provide a light friction fit.
- the root of the projection may be radiused slightly for strength and the mouth of the socket may have a complementary bevel.
- the depth of the socket may be slightly greater than the height of the projection.
- the circular projection and socket are easy to manufacture. They are of effective cross-section to transfer the lead-lag forces.
- An exemplary range of projection diameter is 0.4 mch-1.2 inch and an exemplary range of projection height is 0.1 ⁇ nch-0.3 inch depending on design loading
- the undersides of the retainers may be bonded to the outboard surfaces of the pads and the undersides of the pads then bonded to the flexbeam.
- the flexbeam may be positioned in the outer member 24.
- the two bonded stacks, extending from the respective snubber inner members 30A and 3 OB to the plates 60 A and 60B, are inserted through respective apertures 80A and 80B in the outer member.
- the caps 62A and 62B are then secured to the outer member 24 to precompress the snubber (FIG. 2).
- the preload is such that, given the snubber geometry and the radius of curvature of the surface 36A, 36B, during normal operation the snubber inner members will remain compressively engaged to the associated retainers.
- FIG. 3 shows the system 20 m a strained condition having a pitch angle ⁇ i for a net pitch from neutral of ⁇ - ⁇ ⁇
- Ri designates the radius of curvature of the inner member sphe ⁇ cal surface portions
- H designates the height of contact between the spherical surface portion and the adjacent spacer
- S indicates the separation between the centers of curvature.
- the presence of a positive S provides increased H at a given Ri.
- the non-zero S causes a shear displacement D accommodated by the outer stacks. D is substantially sm( ⁇ - ⁇ o)*S/2.
- the resulting D is 0.211 inch. Because there are typically phase differences between lead/lag and pitch, this increased motion may typically be accommodated with little change to the dampers (e.g , with slight increase in elastomer spacer thickness). If the lead lag motion is simultaneously present, the presence of two opposed dampers means that the pitch-induced increased damping of one damper is largely compensated for by the opposite pitch induced decreased damping of the other damper.
- the increased height also permits a relatively greater wrap angle ⁇ . Where ⁇ i is the half wrap angle of the spacer along the inner member outboard surface. For any given spacer layer, that spacer has a wrap angle ⁇ , (FIG. 1) and a central aperture half angle ⁇ ,.
- the axial and side load pressures P A and P s within a snubber spacer layer is:
- P s (Preload/ ⁇ R,s ⁇ n ,)(s ⁇ n(( ⁇ - ⁇ 0 )(Ro-R.)/(Ro-R ⁇ ))/sm ⁇ ,)
- ( ⁇ i - ⁇ o) is the bea ⁇ ng pitch angle
- Ro (FIG. 1) and Ri (FIG. 3) are respective outer and inner radii of the outboardmost and mboardmost spacers
- the subsc ⁇ pt l designates the particular layer from mboardmost to outboardmost
- ⁇ is ( ⁇ ,+ ⁇ ,)/2.
- the enginee ⁇ ng considerations may include a need to accommodate a given max. bea ⁇ ng pitch angle.
- the combined flexbeam and retainer thickness may be a given (e.g., a minimum thickness dictated by strength considerations). It may be desired to minimize overall snubber/damper height.
- the required ⁇ , for the mboardmost layer can be calculated as desc ⁇ bed above
- the bearing shear stress ⁇ at the max. bea ⁇ ng pitch angle may also be calculated as desc ⁇ bed above.
- the effective snubber height may substantially be related to the sum of R 0 and S/2.
- the available R ⁇ to achieve a given mboardmost layer wrap angle will depend upon S and the combined thickness of the flexbeam, the retainers, and the inner member flange.
- a thickness-minimizing configuration may be iteratively solved based upon these parameters and stress analyses conducted to verify that, at the maximum pitch angle stresses are within acceptable limits.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Architecture (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Bolts, Nuts, And Washers (AREA)
- Clamps And Clips (AREA)
- Braking Arrangements (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006510115A JP4713467B2 (en) | 2003-04-18 | 2004-04-16 | Snubber |
CA002490653A CA2490653C (en) | 2003-04-18 | 2004-04-16 | Snubber |
EP04750209A EP1616111B1 (en) | 2003-04-18 | 2004-04-16 | Snubber |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/418,381 | 2003-04-18 | ||
US10/418,381 US6848886B2 (en) | 2003-04-18 | 2003-04-18 | Snubber |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2004094859A2 true WO2004094859A2 (en) | 2004-11-04 |
WO2004094859A3 WO2004094859A3 (en) | 2005-05-12 |
Family
ID=33159093
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2004/011754 WO2004094859A2 (en) | 2003-04-18 | 2004-04-16 | Snubber |
Country Status (5)
Country | Link |
---|---|
US (1) | US6848886B2 (en) |
EP (1) | EP1616111B1 (en) |
JP (1) | JP4713467B2 (en) |
CA (1) | CA2490653C (en) |
WO (1) | WO2004094859A2 (en) |
Families Citing this family (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040147169A1 (en) | 2003-01-28 | 2004-07-29 | Allison Jeffrey W. | Power connector with safety feature |
US7458839B2 (en) * | 2006-02-21 | 2008-12-02 | Fci Americas Technology, Inc. | Electrical connectors having power contacts with alignment and/or restraining features |
WO2005065254A2 (en) * | 2003-12-31 | 2005-07-21 | Fci Americas Technology, Inc. | Electrical power contacts and connectors comprising same |
EP1704345B1 (en) * | 2004-01-15 | 2012-03-07 | Lord Corporation | Rotary wing aircraft rod end and method of making a helicopter vehicle rod end with a precocked orientation |
US7476108B2 (en) * | 2004-12-22 | 2009-01-13 | Fci Americas Technology, Inc. | Electrical power connectors with cooling features |
US7384289B2 (en) | 2005-01-31 | 2008-06-10 | Fci Americas Technology, Inc. | Surface-mount connector |
US7425145B2 (en) * | 2006-05-26 | 2008-09-16 | Fci Americas Technology, Inc. | Connectors and contacts for transmitting electrical power |
US7641500B2 (en) * | 2007-04-04 | 2010-01-05 | Fci Americas Technology, Inc. | Power cable connector system |
US7905731B2 (en) * | 2007-05-21 | 2011-03-15 | Fci Americas Technology, Inc. | Electrical connector with stress-distribution features |
US7762857B2 (en) | 2007-10-01 | 2010-07-27 | Fci Americas Technology, Inc. | Power connectors with contact-retention features |
US8062051B2 (en) * | 2008-07-29 | 2011-11-22 | Fci Americas Technology Llc | Electrical communication system having latching and strain relief features |
EP2367719B1 (en) * | 2008-12-11 | 2018-09-12 | Sikorsky Aircraft Corporation | Tail rotor blade assembly and elastomeric bearing system motion limiter |
USD610548S1 (en) | 2009-01-16 | 2010-02-23 | Fci Americas Technology, Inc. | Right-angle electrical connector |
USD606497S1 (en) | 2009-01-16 | 2009-12-22 | Fci Americas Technology, Inc. | Vertical electrical connector |
USD664096S1 (en) | 2009-01-16 | 2012-07-24 | Fci Americas Technology Llc | Vertical electrical connector |
USD608293S1 (en) | 2009-01-16 | 2010-01-19 | Fci Americas Technology, Inc. | Vertical electrical connector |
USD640637S1 (en) | 2009-01-16 | 2011-06-28 | Fci Americas Technology Llc | Vertical electrical connector |
US8323049B2 (en) * | 2009-01-30 | 2012-12-04 | Fci Americas Technology Llc | Electrical connector having power contacts |
USD619099S1 (en) | 2009-01-30 | 2010-07-06 | Fci Americas Technology, Inc. | Electrical connector |
US8366485B2 (en) | 2009-03-19 | 2013-02-05 | Fci Americas Technology Llc | Electrical connector having ribbed ground plate |
USD618181S1 (en) | 2009-04-03 | 2010-06-22 | Fci Americas Technology, Inc. | Asymmetrical electrical connector |
USD618180S1 (en) | 2009-04-03 | 2010-06-22 | Fci Americas Technology, Inc. | Asymmetrical electrical connector |
WO2011062639A2 (en) * | 2009-11-23 | 2011-05-26 | Lord Corporation | A rotary wing aircraft bearing for rotary wing aircraft motions |
US8632062B2 (en) * | 2009-11-23 | 2014-01-21 | Lord Corporation | Elastomeric high capacity laminated rotary wing aircraft bearing for rotary wing aircraft |
US9068621B1 (en) | 2010-11-23 | 2015-06-30 | Lord Corporation | Rotary wing aircraft bearing for rotary wing aircraft motions |
US9555880B2 (en) * | 2011-02-09 | 2017-01-31 | Sikorsky Aircraft Corporation | Flexbeam rotor |
US9327832B2 (en) | 2011-10-03 | 2016-05-03 | Bell Helicopter Textron Inc. | Elastomeric bearing with tapered shims |
US9085357B2 (en) | 2011-11-15 | 2015-07-21 | Textron Innovations Inc. | Rotor hub bearing system |
EP2624034A1 (en) | 2012-01-31 | 2013-08-07 | Fci | Dismountable optical coupling device |
US9257778B2 (en) | 2012-04-13 | 2016-02-09 | Fci Americas Technology | High speed electrical connector |
USD718253S1 (en) | 2012-04-13 | 2014-11-25 | Fci Americas Technology Llc | Electrical cable connector |
USD727852S1 (en) | 2012-04-13 | 2015-04-28 | Fci Americas Technology Llc | Ground shield for a right angle electrical connector |
USD727268S1 (en) | 2012-04-13 | 2015-04-21 | Fci Americas Technology Llc | Vertical electrical connector |
US8944831B2 (en) | 2012-04-13 | 2015-02-03 | Fci Americas Technology Llc | Electrical connector having ribbed ground plate with engagement members |
USD751507S1 (en) | 2012-07-11 | 2016-03-15 | Fci Americas Technology Llc | Electrical connector |
US9543703B2 (en) | 2012-07-11 | 2017-01-10 | Fci Americas Technology Llc | Electrical connector with reduced stack height |
USD745852S1 (en) | 2013-01-25 | 2015-12-22 | Fci Americas Technology Llc | Electrical connector |
US10000283B2 (en) * | 2013-03-14 | 2018-06-19 | William L. Hinks | Negative spring compensation for elastomeric bearing torque |
US9285005B2 (en) * | 2013-03-14 | 2016-03-15 | William Lloyd Hinks | Negative spring compensation for elastomeric bearing torque |
USD720698S1 (en) | 2013-03-15 | 2015-01-06 | Fci Americas Technology Llc | Electrical cable connector |
US9334048B2 (en) * | 2013-09-18 | 2016-05-10 | Bell Helicopter Textron Inc. | Elastomeric bearing having tapered layers |
US10233992B2 (en) * | 2017-07-31 | 2019-03-19 | Aktiebolaget Skf | Elastomeric bearing component with wedge-shaped shims |
US10738852B1 (en) * | 2019-03-29 | 2020-08-11 | Aktiebolaget Skf | Laminated bearing assembly with differing shim thicknesses |
US11505312B2 (en) | 2019-04-22 | 2022-11-22 | Lockheed Martin Corporation | Main rotor damper elastomeric rod end |
US10960973B1 (en) * | 2020-01-09 | 2021-03-30 | Aktiebolaget Skf | Radially bisected laminated elastomeric bearing for helicopter pylon mount |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4040690A (en) * | 1975-11-17 | 1977-08-09 | Lord Corporation | Laminated bearing |
US4244677A (en) * | 1978-07-12 | 1981-01-13 | United Technologies Corporation | Cross-beam helicopter rotor with readily replaceable snubber |
US5092738A (en) * | 1990-04-06 | 1992-03-03 | United Technologies Corporation | Flexbeam helicopter rotor with improved snubber-vibration damper between the torque tube and the flexible spar member |
CA2055202C (en) * | 1990-12-17 | 1992-06-18 | Francis E. Byrnes | Snubber-bearing with combined elastomer laminates |
US5188513A (en) * | 1990-12-17 | 1993-02-23 | United Technologies Corporation | Snubber-bearing with combined elastomer laminates |
US6045328A (en) * | 1998-09-23 | 2000-04-04 | Lord Corporation | Fluid damper including flexible damping plate |
-
2003
- 2003-04-18 US US10/418,381 patent/US6848886B2/en not_active Expired - Lifetime
-
2004
- 2004-04-16 EP EP04750209A patent/EP1616111B1/en not_active Expired - Fee Related
- 2004-04-16 JP JP2006510115A patent/JP4713467B2/en not_active Expired - Lifetime
- 2004-04-16 WO PCT/US2004/011754 patent/WO2004094859A2/en active Application Filing
- 2004-04-16 CA CA002490653A patent/CA2490653C/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of EP1616111A4 * |
Also Published As
Publication number | Publication date |
---|---|
EP1616111A2 (en) | 2006-01-18 |
JP2006524608A (en) | 2006-11-02 |
US6848886B2 (en) | 2005-02-01 |
WO2004094859A3 (en) | 2005-05-12 |
CA2490653A1 (en) | 2004-11-04 |
JP4713467B2 (en) | 2011-06-29 |
EP1616111B1 (en) | 2012-08-15 |
CA2490653C (en) | 2008-07-22 |
EP1616111A4 (en) | 2006-06-21 |
US20040208745A1 (en) | 2004-10-21 |
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