ELASTOMERIC HIGH CAPACITY LAMINATED ROTARY WlNG AIRCRAFT BEARING
FOR ROTARY WlNG AIRCRAFT
This appIication claims the benefit of U.S. Provisional Application 63/263,553 filed on
11/23/2009 (EMSTOMERIC HIGH CAPACITY LAMINATED ROTARY WlNG
AIRCRAFT BEARING FOR ROTARY WING AIRCRAFT) which is herein incorporated
by reference.
Field of the invention
The invention relates to the field of rotary wing aircraft such as helicopters. The
invention relates to the field of rotary wing aircraft bearings for connecting rotary wing
vehicle members and providing relative motion between the connecting rotary wing
vehicle members. Mare particularly the invention relates to the Field of elastomeric high
capacity laminated bearings for rotary wing aircraft.
Summary of the Invention
In an embodiment the invention includes a rotary wing aircraft bearing to provide
a constrained relative motion between a first rotary wing aircraft member and a second
rotary wing aircraft member. The bearing includes an etastorneric mold bonded
laminated subassembly, the elastorneric mold bonded laminated subassembly including
a plurality of mold bonded alternating layers of interior nonelastorneric shim members
and interior elastomeric shim members, the interior elastomeric shim members including
a first laminate end elastarneric shim and a distal second laminate end elastomeric
shim. The first laminate end elastomeric shim has a first side mold bonded to a first end
interior nonelastorneric shim member and a second side mold bonded to a first metal
first laminate end structural bond shim. The distal second laminate end eiastomeric
shim having a first side mold bonded to a distal second end interior nonelastorneric
shim member and a second side mold bonded to a second metal distal laminate end
structural bond shim, the elastomeric mold bonded laminated subassembly having an
elastomeric subassembly tensile strength ESTS (preferably 51200 psi) between the first
metal first laminate end structural bond shim and the second metal distal laminate end
structural bond shim. The rotary wing aircraft bearing includes a first end bearing
connector first metal member for connecting to the first rotary wing aircraft member, a
first end structural chemical adhesive epoxy post-elastomeric mold bond between the
first end bearing connector first metal member and the first. metal first laminate end
structural bond shim, the first end structural epoxy bond having an elongation of at least
11 % and a first end tensile strength FETS with FETS 1 ESTS. The rotary wing aircraft
bearing includes a second end bearing connector second metal member for connecting
to the second rotary wing aircraft member, a second end structural chemical adhesive
epoxy post-elastomeric mold bond between the second end bearing connector second
metal member and the second metal first laminate end structural bond shim, the second
end structural epoxy bond having an elongation of at least II %an,d a second end
tensile strength SETS with SETS 2 ESTS.
In an embodiment the invention includes a method of making a rotary wing
aircraft bearing to provide a constrained relative motion between a first rotary wing
aircraft member and a second rotary wing aircraft member. The method includes
providing an elastomeric subassembly bonding mold for receiving a plurality of
alternating layers of interior nonelastomeric shim members and interior elastomeric
shim members, a first metal first laminate end structural bond shim, and a second metal
distal laminate end structural bond shim. The method includes providing a plurality of
interior nonelastomeric shim members. The method includes providing a plurality of
interior elastomeric shim members. The method includes providing a first metal first
laminate end structural bond shim. The method includes providing a second metal
distal laminate end structural bond shim. The method includes disposing the interior
nonelastorneric shim members, the interior elastomeric shim members, the first metal
first laminate end structural bond shim, and the second metal distal laminate end
structural bond shim in the elastomeric subassembly bonding mold with the interior
nonelastomeric shim members and the interior elastorneric shim members alternating
and sandwiched between the first metal first tarninate end structural bond shim and the
second metal distai laminate end structural bond shim. The method includes mold
bonding the interior nonelastomeric shim members, the interior elastomeric shim
members, the first metal first laminate end structural bond shim and the second metal
distal larriinate end structural bond -shim together in the eiastonseric -sabassernbly
bonding mold to provide an elastorneric mold bonded laminated subassembly with the
alternating layers of interior nonelastorneric shim members and interior elastomeric
shim members sandwiched between tt-te first metal first laminate end structurai bond
shim and the second metal distal laminate end structural bond shim, the elastorneric
mold bonded laminated subassembly having an elastorneric subassembly tensile
strength ESTS (51200 psi) between the first metal first laminate end structural bond
shim and the second metal distal laminate end structural bond shim. The method
includes providing a post-elastomeric mold bond structural chemical adhesive epoxy.
The method includes providing a first end bearing connector first metal member for
connecting to the first rotary wing aircraft member. The method includes providing a
second end bearing connector second metal member for connecting to the second
rotary wing aircraft member. The method includes bonding the first end bearing
connector first metal member and the first metal first laminate end structural bond shim
with the post-elastomeric mold bond structural chemical adhesive epoxy to provide a
first end structural epoxy bond having an elongation of at least 11% and a first end
tensile strength FETS (11200 psi). The method includes bonding the second end
bearing connector second metal member and the second metal first laminate end
structural bond shim with the post-elastomeric mold bond structural chemical adhesive
epoxy to provide a second end structural epoxy bond having an elongation of at least
-l I%, and a second end tensile strength SETS (21200psi) with SETS 1 ESTS and FETS
2 ESTS.
In an embodiment the invention includes a rotary wing aircraft bearing to provide
a constrained relative motion between a first rotary wing aircraft member and a second
rotary wing aircraft member. The bearing including an elastomeric mold bonded
laminated subassembly, the elastomeric mold bonded laminated subassembly including
a plurality of mold bonded alternating layers of interior nonelastomeric shim members
and interior elastomeric shim members, the interior elastomeric shim members including
a first laminate end elastomeric shim and a distal second laminate end elastomeric
shim. The first laminate end elastorneric shim has a first side mold bonded to a first end
interior- nonelastomeric shim member and a second side-mold bonded to a first metal
first laminate end structural bond shim. The distal second laminate end elastomeric
shim has a first side mold bonded to a distal second end interior nonelastomeric shim
member and a second side mold bonded to a second metal distal end member, the
elastomeric mold bonded laminated subassembly having an elastomeric subassembly
tensile strength ESTS (11200 psi) between the first metal first laminate end structural
bond shim and the second metal distal end member. The rotary wing aircraft bearing
including a first end bearing connector first metaf member for connecting to the first
rotary wing aircraft: member, a first end structural chemical adhesive epoxy postelastorneric
mold bond between the first end bearing connector first metal member and
the first metal first laminate end structural bond shim, the first end structural epoxy bond
having an elongation of at least of at least 4 4% and a first end tensile strength FETS 2
ESTS. The second metal distal end member mechanicaliy grounded to the second
rotary wing aircraft member.
In an embodiment the invention includes a method of making a rotary wing
aircraft bearing to provide a constrained relative motion between a first rotary wing
aircraft member and a second rotary wing aircraft member. The method includes
providing an elastorneric subassembly bonding mold for receiving a plurality of
alternating layers of interior nonelastomeric shim members and interior elastomeric
shim members, a First metal first laminate end structural bond shim, and a second metal
distal end member. The method includes providing a plurality of interior' nonelastomeric
shim members. The method includes providing a pfurality of interior elastomeric shim
members. The method includes providing a first metal first: laminate end structural bond
shim. The method includes providing a second metal distal end member. The method
includes disposing the interior nonelastomeric shim members, the interior elastomeric
shim members, the first metal first laminate end structural bond shim, and the second
metal distal end member in the elastomeric subassembly bonding mold with the interior
nanelastomeric shim members and the interior elastomeric shim members alternating
and sandwiched between the first metal first laminate end structural bond shim and the
second metal distal end member. The method includes mold bonding the interior
noneiastorrreric shim members, the interior elastomeric shim rrrernbe~st,h e firs4 fftetal
first laminate end structural bond shim and the second metal distal end member
together in the elastomeric subassembly bonding mold to provide an elastomeric mold
bonded laminated subassembly with the alternating layers of interior nonelastomeric
shim members and interior elastomeric shim members sandwiched between the first
metal first laminate end sfructural bond shim and the second metal distal end member,
the elastomeric mold bonded laminated subassembly having an elastomeric
subassembly tensile strength ESTS between the first metal first laminate end structural
bond shim and the second metal distal end member. The method includes providing a
post-elastorneric mold bond structural chemical adhesive epoxy. The method includes
providing a first end bearing connector first metal member for connecting to the first
rotary wing aircraft member. The method includes bonding the first end bearing
connector first metal member and the first metal first laminate end structural bond shim
with the post-elastorneric mold bond structural chemical adhesive epoxy to provide a
first end structural epoxy bond having an elongation of at least 11% and a first end
tensile strength FETS with FETS 2 ESTS.
It is to be understood that both the foregoing general description and the
following detailed description are exemplary of the invention, and are intended to
provide an overview or framework for understanding the nature and character of the
invention as it is claimed. The accompanying drawings are included to provide a further
understanding of the invention, and are incorporated in and constitute a part of this
specification. The drawings illustrate various embodiments of the invention, and
together with the description serve to explain the principals and operation of the
invention.
Detailed Description of the Preferred Embodiment
Additional features and advantages of the invention will be set forth in the
detailed description which follows, and in part will be readily apparent to those skitled in
the art from that description or recognized by practicing the invention as described
herein,-including the detailed -description which -.foilow$, -the claims; as well -as theappended
figures.
Reference will now be made in detail to the present preferred embodiments of
the invention, examples of which are illustrated in the ac;campanying figures.
In an embodiment the invention includes a rotary wing aircraft bearing 20 to
provide a constrained relative motion between a first rotary wing aircraft member 22 and
a second rotary wing aircraft member 24. The bearing includes an elastomeric mold
bonded laminated subassembly 26, the elastomeric mold bonded laminated
subassembly 26 including a plurality of mold bonded alternating layers of interior
nonelastomeric shim members 28 and interior elastomeric shim members 30, the
interior elastomeric shim members 30 including a first laminate end elastorneric shim
30' and a distat second laminate end elastomeric shim 30". The first laminate end
elastomeric shim 30' has a first side 100 mold bonded to a first end interior
nonelastomeric shim member 102 and a second side 104 mold bonded to a first metal
first laminate end structural bond shim 106. The distal second laminate end etastomeric
shim 30" has a first side 108 mold bonded to a distal second end interior
nonelastomeric shim member 110 and a second side 112 mold bonded to a second
metal distal laminate end structural bond shim 114, the elastomeric mold bonded
laminated subassembly 26 having an elastomeric subassembly tensile strength ESTS
(preferably ESTS.51200 psi) between the first metal first laminate end structural bond
shim 106 and the second metal distat laminate end structural bond shim 114. The
rotary wing aircraft bearing 20 includes a first end bearing connector first metal member
I1 6 for connecting to the first rotary wing aircraft member, a first end structural chemical
adhesive epoxy post-elastorneric mold bond 118 between the first end bearing
connector first metal member 116 and the first metal first laminate end structural bond
shim 106, the first end structural epoxy bond 1 18 having an elongation of at least 1 I %.
Preferably the first end structural epoxy bond I18 has an elongation of at least at teast
17%, preferably at least 99%, preferably with elongation ranges from 11 to 27%'
preferably 17-26%' and preferably 1 9-25%. Preferably the first end structural epoxy
bond 1-1 8 has-a-first end-tensile slrength FETG-2750psi, preferably r3000psil and preferably in the
adhesive strength range of 3000 to 5000 psi in shear and tension. The rotary wing
aircraft bearing 20 includes a second end bearing connector second metal member 120
for connecting to the second rotary wing aircraft member, a second end structural
chemical adhesive epoxy post-elastorneric mold bond 122 between the second end
bearing connector second metal member 120 and the second metal first laminate end
structural bond shim 114, the second end structural epoxy bond 122 having an
elongation of at least 7 1%. Preferably the second end structural epoxy bond 'I22 has
an elongation of at least 17%, preferably at least 19%, preferably with elongation ranges
from 11 to 27%, preferably 17-26%, and preferably 19-25%. Preferably the second end
structural epoxy bond 122 has a second end tensile strength SETS (21200 psi,
preferably r2500psi, preferably 22750psi, preferably 23000psi, preferably in the
adhesive strength range of 3000 to 5000 psi in shear and tension) with SETS 2 ESTS.
Preferably SETS 21200 psi, preferably r2500psil preferably 12750psi, preferably
13000psi, preferably in the adhesive strength range of 3000 to 5000 psi in shear and
tension. In an embodiment the first end structural chemical adhesive epoxy postelastomeric
mold bond is comprised of a spherical shell segment. Preferably the
spherical shell segment consists essentially of a maintained thickness cured structural
chemical adhesive in the shape of a segment of a spherical shell with a maintained
thickness disposed between spherical segment surfaces of the first end bearing
connector first metal member and the first metal first laminate end structural bond shim.
In an embodiment the second end structural chemical adhesive epoxy postelastomeric
mold bond 322 is comprised of a spherical shell segment, and preferably
consists essentially of a maintained thickness cured structural chemical adhesive in the
shape of a segment of a spherical shell with a maintained thickness disposed between
spherical segment surfaces of the second end bearing connector first metal member
and the second metal first laminate end ~tructurabl ond shim. Preferably the first end
bearing connector first metal member 116 and the first metal first laminate end
structural bond shim A06 consist essentiajiy of the-same metal composition. --Preferably
the second end bearing connector second metal member 120 and the second metal first
laminate end structural bond shim 114 consist essentially of the same metal
composition.
In an embodiment the invention includes a method of making a rotary wing
aircraft bearing 20 to provide a constrained relative motion between a first rotary wing
aircraft member 22 and a second rotary wing aircraft member 24. The method includes
providing an elastomeric subassembly bonding mold 60 for receiving a plurality of
alternating layers of interior nonelastomeric shim members 28 and interior elastomeric
shim members 30, a first metal first laminate end structural bond shim 106, and a
second metal distal laminate end structural bond shim 114. The method includes
providing a pturatity of interior nonelastameric shim members 28. The method includes
providing a plurality of interior elastomeric shim members 30. The method includes
providing a first metal First laminate end structural bond shim 106. The method includes
providing a second metal distal laminate end structural bond shim 114. The method
includes disposing the interior nonelastorneric shim members 28, the interior
elastomeric shim members 30, the first metal first laminate end structural bond shim
106, and the second metal distal laminate end structural bond shim A14 in the
elastomeric subassembly bonding mold 60 with the interior nonelastomeric shim
members and the interlor elastomeric shim members alternating and sandwiched
between the first metal first laminate end structural bond shim 106 and the second
metal distal laminate end structural bond shim I A4. The method includes mold bonding
the interior nonelastameric shim members 28, the interior elastomeric shim members
30, the first metal first laminate end structural bond shim 106 and the second metal
distal laminate end structural bond shim 114 together in fke elastomeric subassembly
bonding mold 60 to provide an elastomeric mold bonded laminated subassembly 26
with the alternating layers of interior nonelastorneric shim members 28 and interior
elastomeric shim members 30 sandwiched between the first metal first laminate end
structural bond shim 106 and the second metal distal laminate end structural bond shim
114, the elastorneric mold bonded laminated subassembly 26 having an elastorneric
subassembly tensile strength ESTS-$Sl2OO- psi)- between the first metal,-first larnirtate
end structural bond shim 106 and the second metal distal laminate end structural bond
shim 114, preferably with ESTS (21200 psi). The method includes providing a postelastomeric
mold bond structural chemical adhesive epoxy 150. The method includes
providing a first end bearing connector first metal member I I 6 for connecting to the
first rotary wing aircraft member. The method includes providing a second end bearing
connector second metal member 120 far connecting to the second rotary wing aircraft
member. The method includes bonding the first end bearing connector first metal
member 146 and the first metal first laminate end structural bond shimlo6 with the
post-elastomeric mold bond structural chemical adhesive epoxy to provide a first end
structural epoxy bond 118 having an elongation of at least 11% and a first end tensile
strength FETS. Preferably the first end structural epoxy bond 418 elongation is at least
17%, preferably at least 1996, preferably with elongation ranges from 11 to 27%,
preferably 17-26%, and preferably 19-25%. Preferably the first end structural epoxy
bond first end tensile strength FETS 21200 psi, preferably 225OOpsi, preferably
r2750psi, preferably >3000psi, preferably in the adhesive strength range of 3000 to
5000 psi in shear and tension. The method includes bonding the second end bearing
connector second metal member 120 and the second metal first laminate end structural
bond shim 114 with the post-elastomeric mold bond structurat chemical adhesive epoxy
150 to provide a second end structural epoxy bond 122 having an elongation of at least
11%. Preferably the first end structural epoxy bond 122 elongation is at least 17%,
preferably at least 19%, preferably with elongation ranges from 11 to 27%, preferably
17-26%, and preferably 19-25%. Preferably the second end structural epoxy bond has
a second end tensile strength SETS 21200 psi, preferably r2500psi, preferably
12750psi, preferably 23000psi, preferably in the adhesive strength range of 3000 to
5000 psi in shear and tension, with SETS 2 ESTS and FETS 2 ESTS. In an
embodiment the method includes providing a plurality of spherical shell segment interior
noneiastomeric shim members 28, providing a first spherical shell segment metal first
laminate end structural bond shim 106, and providing a second spherical shell segment
metal distal laminate end structural bond shim 114. Preferably the method includes
maintaining a post-elastomeric mold bond structural chemical adhesive bond thickness
between the first- end bearing -cmnnector *first metal member I A 6 and-the first metalpfirst
laminate end structural bond shim 106 during an adhesive bond cure time to provide a
first spherical shell segment bond 11 8, and maintaining a post-elastomeric mold bond
structural chemical adhesive bond thickness between the second end bearing
connector second metal member 120 and the second metal second laminate end
structural bond shim 124 during the adhesive bond cure time to provide a second
spherical shell segment bond 122. Preferably the first end bearing connector first metal
member and the first metal first laminate end structural bond shim are comprised of a
first metal composition. Preferably the second end bearing connector second metal
member and the second metal first laminate end structural bond shim are comprised of
a second metal composition. Preferably the method includes maintaining a pastelastomeric
mold bond structural chemical adhesive bond thickness between the first
end bearing connector first rnetaf member and the first metal first laminate end
structural bond shim during an adhesive bond cure time to provide a first end pastelastomeric
mold bond structural chemical adhesive bond thickness, and maintaining a
post-efastomeric mold bond structural chemical adhesive bond thickness between the
second end bearing connector second metal member and the second metal second
laminate end structural bond shim during the adhesive bond cure time to provide a
second end post-elastomeric mold bond structural chemical adhesive bond thickness.
Preferably the method includes providing a fixturing jig 152, and disposing the rotary
wing aircraft bearing 20 in the fixturing jig during the adhesive bond cure time to
maintain bond thickness.
In an embodiment the invention includes a rotary wing aircraft bearing 20 to
provide a constrained relative motion between a first rotary wing aircraft member and a
second rotary wing aircraft member. The bearing 20 includes an elastorneric mold
bonded laminated subassembly 26, the elastorneric. mold bonded laminated
subassembly including a plurality of mold bonded alternating layers of interior
nonelastomeric shim members 28 and interior elastorneric shim members 30, the
interior elastomeric shim members 30 including a first laminate end elastomeric shim
30' and a distal second laminate end elastomeric shim 30". The first laminate end
e!mforneric-shim 3@ -has- as-fi rst --side 400 - madd bonded - fa a first-.end - interior
nonelastomeric shim member 102 and a second side 104 mold bonded to a first rneta!
first laminate end structural bond shim 106. The distal second tarninate end elastorneric
shim 30" has a first side 108 mold bonded to a distal secand end interior
nonelastomeric shim member 110 and a second side 112 mold bonded to a second
metal distal end member, the ekastomeric mold bonded Iarninated subassembly having
an elastorneric subassembly tensile strength ESTS (51200 psi) between the first metal
first laminate end structural bond shim 106 and the second metal distal end member.
The rotary wing aircraft bearing includes a first end bearing connector first metal
member 1 'l6 for connecting to the first rotary wing aircraft member, a first end structural
chemical adhesive epoxy post-elasiorneric mold bond 14 8 between the first end bearing
connector first metal member 116 and the first metal first laminate end structural bond
shim 106, the first end structural epoxy bond 1 18 having an elongation of at least 1 I %
and a first end tensile strength FETS 2 ESTS. Preferably, the first end structural epoxy
bond has an elongation of at least 1796, preferably at least 19%, preferably with
elongation ranges from 1A to 27%, preferably 17-26%, and preferably 19-25%.
Preferably, the first end structural epoxy bond has first end tensile strength FETS 21200
psi, preferably 22500psi, preferably 22750psi, preferably 23000psi, preferably in the
adhesive strength range of 3000 to 5000 psi in shear and tension. Preferably the
second metal distal end member is mechanically grounded to the second rotary wing
aircraft member. Preferably the first end structural chemical adhesive epoxy postelastorneric
mold bond 118 is comprised of a spherical shell segment, and preferably
consists essentially of a maintained thickness cured structural chemical adhesive in the
shape of a segment of a spherical shell with a maintained thickness disposed between
spherical segment surfaces of the first end bearing connector first metal member and
the first metal first laminate end structural bond shim. Preferably the first end structural
chemical adhesive epoxy post-elastomeric mold bond 118 is tubular, and preferably
consists essentially of a maintained thickness cured structural chemical adhesive tube
with a maintained thickness disposed between surfaces of the first end bearing
connector first metal member 116 and the first metal first laminate end structural bond
shim 106. Preferably the first end structural chemical adhesive epoxy post-elastorneric
mold bond 'l18 is -comprised -of a conical shell segment, and preferably -consists
essentially of a maintained thickness cured structural chemical adhesive conical shell
segment with a maintained thickness disposed between sutfaces of the first end bearing
connector first metal member and the first metal first laminate end structural bond shim.
Preferably the first end bearing connector first metal member and the first metal first
laminate end structural bond shim consist essentially of the same metal composition.
Preferably the second metal distal end member is comprised of a tube. Preferably the
distal second end interior nonelastomeric shim member has a shim thickness Tlnteriorshim
and the second metal distal end member tube has a tube thickness Ttubew ith Ttube> 5
TlntenarshlmP. referably the first metal first laminate end structural bond shim has a shim
thickness Te*eriorshrm with Ttube > 5 Te*erioEhlm. Preferably the first end interior
nonelastomeric shim member has a shim thickness TLnterioishlamn d the first metal first
laminate end strucZura1 bond shim has a shim thickness Texteriorshwlmit h Te*eriorshi2m
Tinteriorshirn.
In an embodiment the invention includes a method of making a rotary wing
aircraft bearing to provide a constrained relative motion between a first rotary wing
aircraft member and a second rotary wing aircraft member. The method inctudes
providing an elastomeric subassembly bonding mold for receiving a plurality of
alternating layers of interior nonelastomeric shim members and interior elastomeric
shim members, a first metal first laminate end structural band shim, and a second metal
distal end member. The method includes providing a plurality of interior nonelastorneric
shim members. The method includes providing a plurality of interior elastomeric shim
members. The method includes pravidjng a first metal first laminate end structural bond
shim. The method includes providing a second metal distal end member. The method
includes disposing the interior nonelastomeric shim members, the interior elastomeric
shim members, the first metal first laminate end structural bond shim, and the second
metal distal end member in the elastomeric subassembly bonding mold with the interior
nonelastomeric shim members and the interior elastomeric shim members alternating
and sandwiched between the first metal first laminate end structural bond shim and the
second metal distal end member. The method includes mold bonding the interior
nonelastomerie shim members, the interisr- elastam-eric shim-r neru~berst,h e first -metal
first laminate end structural bond shim and the second metal distal end member
together in the elastomeric subassembly bonding mold to provide an elastorneric mold
bonded laminated subassembly with the alternating layers of' interior nonelastomeric
shim members and interior elastomeric shim members sandwiched beheen the first
metal first laminate end structural bond shim and the second metal distal end member,
the elastomeric mold bonded laminated subassembly having an elastomeric
subassembly tensile strength ESTS (51200 psi) between the first metal first laminate
end structural bond shim and the second metal distal end member. The method
inctudes providing a post-elastomeric mold bond structural chemical adhesive epoxy.
The method includes providing a fit-st end bearing connector first metal member for
connecting to the first rotary wing aircraft member. The method includes bonding the
first end bearing connector first metal member and the first metal first laminate end
structural bond shim with the post-elastomeric mold bond structurai chemical adhesive
epoxy to provide a first end structural epoxy bond having an elongation of at least 1 -I%,
and a first end tensile strength FETS with FETS 2 ESTS. Preferably first end structural
epoxy bond has an elongation of at least 1796, preferably at least 19%, preferably with
elongation ranges from 11 to 27%, preferably 17-26%, and preferably 19-25%.
Preferably the first end tensile strength FETS 21200 psi, preferably r2500psi, preferably
22750psi, preferably r3000psi, preferably in the adhesive strength range of 3000 to
5000 psi in shear and tension. Preferably the method includes providing a plurality of
spherical shell segment interior nonelastomeric shim members, and providing a first
spherical shell segment metal first laminate end structural band shim. Preferably the
method includes maintaining a post-elastorneric mold bond structural chemical adhesive
bond thickness beheen the first end bearing connector first metal member and the first
metal first laminate end structural bond shim during an adhesive bond cure time to
provide a first spherical shell segment band. Preferably the first end bearing connector
first metal member and the first metal first laminate end structural bond shim are
comprised of a first metal composition. Preferably method the includes maintaining a
post-elastomeric mold bond structural chemical adhesive bond thickness between the
first end bearing connector first metal member and the first metal first laminate end
structural=~brindsh im during an adhesive bond-.cure-i ime lo provide a first en& postelastomeric
mold bond structural chemical adhesive bond thickness. Preferably the
method includes providing a fixturing jig, disposing the rotary wing aircraft bearing in the
fixturing jig during the adhesive bond cure time. In an embodiment the first end
structural chemical adhesive epoxy post-elastomeric mold bond is comprised of a
spherical shell segment, and preferably consists essentially of a maintained thickness
cured structural chemical adhesive in the shape of a segment of a spherical shell with a
maintained thickness disposed between spherical segment surfaces of the first end
bearing connector first metal member and the first metal first laminate end structural
bond shim. Preferably the first end structural chemical adhesive epoxy post-elastomeric
mold bond is tubular, and preferably consists essentially of a maintained thickness
cured structural chemical adhesive tube with a maintained thickness disposed between
surfaces of the first end bearing connector first metal member and the first metal first
laminate end structural bond shim. In an embodiment the first end structural chemical
adhesive epoxy post-elastorneric mold bond is comprised of a conical shell segment,
and preferably consists essentially of a maintained thickness cured structural chemical
adhesive conical shell segment with a maintained thickness disposed between surfaces
of the first end bearing connector first metal member and the first rnetaf first laminate
end structural bond shim. In an embodiment the second metal distal end member is
comprised of a tube. Preferably the distal second end interior nonelastorneric shim
member has a shim thickness Tlnterrorshim and the second metal distal end member tube
has a tube thickness Ttubwe ith Ttube> 5 Tlnterio,,h,m.Preferabtyt he first metal first laminate
end structural bond shim has a shim thickness Texteriorshwlmith Ttube> 5 Texteftorshim.
Preferably the interior nonelastorneric shim members have a shim thickness Tlnterlorshlm
and the first metal first laminate end structural bond shim has a shim thickness
Texterionhtrn with Texteriorshlm 2 Tinterlorshlm.
The structural chemical adhesive epoxy post-elastomeric mold bond preferably
has the high strengths and elongations before permanent yielding occurs. Preferably
the structural chemical adhesive epoxy post-elastomeric mold bond is an the order of
twice as strong as the elastomeric mold bonded laminated subassembly, preferably at
lea-st%m ,and half times as-strong, a d -preferably- at leastthree -tin1e-sWasst rong.
Preferably the structural chemical adhesive epoxy post-elastomeric mold bond
structural epoxy bond has the elongation of at least 11% to fracture, preferably with we
need elongations of in the range of about25%. Preferably the structural chemical
adhesive epoxy post-elastomeric mold bond elongation of at least I It %, is at teast 17%,
preferably at least 19%, preferabty with elongation ranges from 11 to 27%, preferably
17-26%, and preferably 19-25%. The structural chemical adhesive epoxy postelastomeric
mold bond preferably has the tensile strength greater than 1200 psi,
preferably 22500psi, preferably 22750psi, preferably 23000psi, and preferably in the
adhesive strength range of 3000 to 5000 psi in shear and tension, and preferably the
structural adhesive has a high enough elongation-to-fracture to survive the elastic
flexing of the bonded to rotary wing aircraft member with the elastomeric mold bonded
laminated subassembly experience initiated damage.
Preferably the structurat chemical adhesive epoxy post-elastameric mold bonds
are formed from high elongation, high strength epoxies with favorable cures that do not
harm vulcanize-bonded elastorneric packages and exceed the elastomer strength, with
the epoxies elongation comparable with the rotary wing aircraft member surviving longer
than the elastomer subassembly.
In an embodiment the structural chemical adhesive epoxy post-elastorneric mold
bonds is formed from an EpibondTMa dhesive epoxy, preferably EpibondrM 1590. In an
embodiment the structural chemical adhesive epoxy post-elastorneric mold bonds is
formed from an HysolTM adhesive epoxy, preferably HysolW 9335.3 Preferably the
epoxies include beads, preferably glass beads, such as .005 inch diameter gtass beads.
In an embodiment the invention includes utilizing existing fully vulcanize elastomeric
bonding molds and modifying such to receive the subassemblies without the normal
rotary wing aircraft members in the mold. The metal laminate end structural bond shims
bonding shims are vulcanize-bonded on one sulface and then later outside the mold
structurally bonded on the other.
Prefe-rably the rnater-ial metal-laminate end- structural bonding-skim is of the same
type of the major metal rotary wing aircraft member it is structurally bonded to. In
preferred embodiments using newly designed molds that do not accept the rotary wing
aircraft members and the inner and outer laminate end structural bonding shims are not
as thick as the needed to fit an existing part mold. Fig. I illustrates a spherical bearing
subassembly for an existing part mold with the epoxy bonding shims having a thickness
greater than the interior nonelastomeric shims.
When elastorneric mold bonded laminated subassembly vulcanization bonding is
complete, the end bonding shims are treated with an epoxy metal preparation. The
metal preparation preferably does not negatively impact the elastomer subassembly
package, yet ensures a reliable structural bond. Contaminants need to be cleaned from
the bonding shim and the preferred dimensional characteristics of the structural bond
with about .005 - .010 inch bond tine clearance are provided.
Preferably fixtures such as fixturing jigs 152 are provided to maintain epoxy bond
dimensional characteristics, preferably with rotary wing aircraft bearing disposed in a
fixturing jig during the adhesive bond cure time. Preferably with tubular bearings such
as ilfustrated in Fig. 2-3 with tube forms and low angle conical packages utilize a low
angle conical bonding surface that can be fixated to an axial dimension and preferably a
clocking dimension to provide a bond tine characteristic centered about .0075 inch thick
resultant structural bond line and orientation between the bonded inner and outer
members. Preferably two degrees of freedom are locked in space per structural bond
joint. Preferably spherical thrust-type bearings and quasi-flat bearings utilize structural
bonding fixtures to assure the bond [ine characteristic centered about .0075 inch
nominal bond line exists. Fig. 4 illustrates a spherical bearing subassembly such as
shown in fig. 'l between the first end bearing connector first metal member and the
second end bearing connector second metal member fur the epoxy bonds. Fig. 5
illustrates such held in a fixturing jig 152 to maintain the epoxy bonds dimensions while
the epoxy is curing.
In embodiments the uncured wet epoxy; fixture, inner--member, outer member
and elastomeric subassembly package are oven cured to provide the epoxy bond. The
temperature and time should minimally impact the elastomer package based on design
allowables, preferably with cure times such as three hours at 150 degree F or four hours
at 140 degree F. Preferably the cure temperature is controlled to assure a full epoxy
cure and to prevent undue heating of the elastomer subassembly package.
In preferred methods the mold and the elastomeric subassembly are designed
together. Preferably the metal materials either side of the structural epoxy bond are
maintained in common to inhibit thermal stresses in the structural bond.
Fig. 6 illustrates a spherical bearing elastomeric mold bonded laminated
subassembly with a first end bearing connector first metal member for structural
chemical adhesive post-elastomeric mold bonding between the first end bearing
connector first metal member and the first metal first laminate end structural bond shim.
Fig 7 illustrates embodiments of making bearings with spherical bearing etastorneric
mold bonded laminated subassemblies.
It will be apparent to those skilled in the art that various modifications and
variations can be made to the invention without departing from the spirit and scope of
the invention. Thus, it is intended that the invention cover the modifications and
variations of this invention provided they come within the scope of the appended claims
and their equivalents. It is intended that the scope of differing terms or phrases in the
claims may be fulfilled by the same or different structure(s) or step(s).

Claims:
1.
A rotary wing aircraft bearing to provide a constrained relative motion between a first
rotary wing aircraft member and a second rotary wing aircraft member,
an elastomeric mold bonded laminated subassembly, said elastomeric mold
bonded laminated subassembly including a plurality of mold bonded alternating layers
of interior nonelastorneric shim members and interior elastomeric shim members, said
interior elastomeric shim members including a first laminate end elastorneric shim and a
distal second laminate end elastomeric shim,
said first laminate end elastomeric shim having a first side mold bonded to a first
end interior nonelastorneric shim member and a second side mold bonded to a first
metal first laminate end structural bond shim,
said distal second laminate end etastomeric shim having a first side mold bonded
to a distal second end interior nonelastorneric shim member and a second side mold
bonded to a second metal distal laminate end structural bond shim, said elastorneric
mold bonded laminated subassembly having an elastomeric subassembly tensile
strength ESTS between said first metal first laminate end structural bond shim and said
second metal distal laminate end structural bond shim,
said rotary wing aircraft bearing including a first end bearing connector first metal
member for connecting to said first rotary wing aircraft member, a first end structural
chemical adhesive post-elastomeric mold bond between said first end bearing
connector first metal member and said first metal first laminate end structural bond
shim, said first end st~ucturaf bond having an elongation of at least I f %, and a first end
tensile strength FETS with FETS 1: ESTS,
said rotary wing ajrcraff bearing including a second end bearing connectur
second metal member for connecting to said second rotary wing aircraff member, a
second end structural chemical adhesive post-elastomeric mold bond between said
second end bearing connector second metal member and said second metal first
laminate end structural bond shim, said second end structural bond having an
elongation of at least 1 'I %, and a second end tensile strength SETS with SETS 2 ESTS.
2. A rotary-wing aircraft bearing 3s claimed in dairn-I , .wherein said first end--structurat
chemical adhesive post-elastomeric mold band is comprised of a spherical shell
segment.
3. A rotary wing aircraft bearing as claimed in claim I, wherein said second end
structural chernicat adhesive post-elastorneric mold bond is comprised of a spherical
shell segment.
4. A rotary wing aircraft bearing as claimed in claim 1, wherein said first end bearing
connector first metal member and said first metal first laminate end structural bond shim
consist essentially of the same metal composition,
5. A rotary wing aircraft bearing as claimed in claim 1, wherein said second end bearing
connector second metal member and said second metal first laminate end structural
bond shim consist essentially of the same metal composition.
6.
A method of making a rotary wing aircraft bearing to provide a constrained relative
motion between a first rotary wing aircraft member and a second rotary wing aircraft
member, said method including:
providing an elastomeric subassembiy bonding mold for receiving a plurality of
alternating layers of interior nonelastomeric shim members and interior elastomeric
shim members, a first metal first laminate end structural bond shim, and a second metal
distal laminate end structural bond shim,
providing a plurality of interior nonetastomeric shim members,
providing a plurality of interior elastomeric shim members,
providing a first metat first laminate end structural bond shim,
providing a second metal distal laminate end structural bond shim,
disposing said interior nonelastomeric shim members, said interior elastomeric
shim members, said first metal first laminate end structural bond shim, and said second
metal distal laminate end structural bond shim in said elastorneric subassembly bonding
mald with said interior nonelastornerjc shjm members and said interior elastomeric shim
members alternating and sandwiched between said first metal first laminate end
structural bond shim and said second metal distal laminate end structural bond shim,
mold bonding said interior nonelastomeric shim members, said interior
elastomeric shim members, said first metal first laminate end structural bond shim and
said second metal distal laminate end structural bond shim together in said efastomeric
subassembly bonding mold to provide an etastorneric mold bonded laminated
subassembly with said alternating layers of interior nonelastorneric shim members and
interior elastomeric shim members sandwiched between said first metal first laminate
end structural bond shim and said second metal distal laminate end structural bond
shim, said elastomeric mald bonded laminated subassembly having an elastorneric
subassembly tensile strength ESTS between said first metal first laminate end structural
bond shim and said second metal distal laminate end structural bond shim,
providing a post-elastomeric mold bond structural chemical adhesive,
providing a first end bearing connector first metal member,
providing a second end bearing connector second metal member,
banding said firstend bearing connecto~ first metal member and said -fiat metal first
laminate end structural bond shim with said post-elastomeric mold bond structural
chemical adhesive to provide a first end structural bond having an elongation of at least
1 I %, and a first end tensile strength FETS,
and bonding said second end bearing connector second metal member and said
second metal first laminate end structural bond shim with said post-elastorneric mold
bond structural chemical adhesive to provide a second end structural bond having an
elongation of at least 1 I %, and a second end tensile strength SETS with SETS 2 ESTS
and FETS 2 ESTS.
7. A. method of making a rotary wing aircraft bearing as claimed in claim 6, wherein
providing a plurality of interior nonelastomeric shim members, providing a first metal first
laminate end structural bond shim, and providing a second metal distal laminate end
structurat bond shim,
includes providing a plurality of spherical shell segment interior nonelastomeric
shim members,
providing a first spherical shell segment metal first laminate end structural bond
shim,
and providing a second spherical shell segment metal distal laminate end
structural bond shim.
8. A method of making a rotary wing aircraft bearing as claimed in claim 7 induding
maintaining a post-elastometic mold band structural chemical adhesive bond thickness
between said first end bearing connector first metal member and said first metal first
laminate end structural bond shim during an adhesive bond cure time to provide a first
spherical shell segment bond, and maintaining a post-elastomeric mold bond structural
chemical adhesive bond thickness between said second end bearing connector second
metal member and said second metal second laminate end structural bond shim during
said adhesive bond cure time ta provide a second spherical shell segment bond.
9. A nrethsd"as cfairrled in claim 6 wherein said3first-end bearing conne&or-first- metal
member and said first metal first laminate end structural bond shim are comprised of a
first metal composition.
10. A method as claimed in claim 6 wherein said second end bearing connector second
metal member and said second metal first laminate end structural bond shim are
comprised of a second metal composition.
11. A method as claimed in claim 6 including maintaining a post-elastomeric mold bond
structural chemical adhesive bond thickness between said first end bearing connector
first metal member and said first: metal first laminate end structural bond shim during an
adhesive bond cure time to provide a first end post-elastomeric mold bond structural
chemical adhesive bond thickness,
and maintaining a post-elastomeric mold bond structural chemical adhesive bond
thickness between said second end bearing connector second metal member and said
second metal second laminate end structural bond shim during said adhesive bond cure
time to provide a second end post-elastomeric mold bond structural chemical adhesive
bond thickness.
12. A method as claimed in claim 11, including a providing a fixturing jig, disposing said
rotary wing aircraft bearing in said fixturing jig during said adhesive bond cure time.
13.
A rotary wing aircraft bearing to provide a constrained refative motion between a first
rotary wing aircraft member and a second rotary wing aircraft member, said bearing
including
an elastomeric mold bonded laminated subassembly, said elastorneric mold
bonded laminated subassembly including a plurality of mold bonded alternating layers
of interior nonelastomeric shim members and interior elastomeric shim members, said
interior elastomeric shim members including a first laminate end elastomeric shim and a
distal second laminate end elastorneric shim,
said first laminate end elastometic shim having a first side mold bonded to a first
end interior nonelastomeric shim member and a second side mold bonded to a first
metal first laminate end structural bond shim,
said distal second laminate end elastorneric shim having a first side mold bonded
to a distal second end interior nonelastorneric shim member and a second side mold
bonded to a second metal distal end member, said elastomeric mofd bonded laminated
subassembly having an elastorneric subassembly tensile strength ESTS between said
first metal first laminate end structural bond shim and said second metal distal end
member,
said rotary wing aircraft bearing including a first end bearing connector first metal
member for connecting to said first rotary wing aircraft member, a first end structural
chemical adhesive post-elastomeric mold bond between said first end bearing
connector first metal member and said first metal first laminate end structural bond
shim, said first end structural bond having an elongation of at least of at least 1I %and,
a first end tensile strength FETS r ESTS,
said second metal distal end member mechanically grounded to said second
rotary wing aircraft member.
14. A rotary wing aircraft -4earln-g -as -claimed in- elaim 13, wherein said first end
structural chemical adhesive post-elastomeric mold bond is comprised of a spherical
shell segment.
15. A rotary wing aircraft bearing as claimed in claim 13, said first end structural
chemical adhesive post-elastorneric mold bond is tubular.
16. A rotary wing aircraft bearing as claimed in claim 15, said first end structural
chemical adhesive post-elastomeric mold bond is comprised of a conical shell segment.
1 7- A rotary wing aircraft bearing as claimed in claim 'I 3, wherein said first end bearing
connector first metal member and said first metal first laminate end structural bond shim
consist essentially of the same metal composition,
18. A rotary wing aircraft bearing as claimed in claim 13, wherein said second metal
distal end member is comprised of a tube.
19. A rotary wing aircraft bearing as claimed in claim 9 8 wherein said distal second end
interior nonelastomeric shim member has a shim thickness Tinteriorshaimnd, said second
metal distal end member tube has a tube thickness Ttubew ith Ttube> 5 Tinterjorshim
20. A rotary wing aircraft bearing as claimed in claim 18 wherein said first metal first
laminate end structural bond shim has a shim thickness Texteriorshwimith Ttube> 5
21. A rotary wing aircraft bearing as claimed in claim 13 wherein said first end interior
nonelastorneric shim member has a shim thickness TinterioEhim and said first metal first
farninate end structural bond shim has a shim thickness Texteriarshwimith Teaeriorsh2im
22.
A method of making a rotary wing aircraft bearing to provide a constrained relative
motion between a first rotary wing aircraft member and a second rotary wing aircraft
member, said method including:
providing an elastomeric subassembly bonding mold for receiving a plurality of
alternating layers of interior nonelastomeric shim members and interior elastorneric
shim members, a first metal first laminate end structural bond shim, and a second metal
distal end member,
providing a plurality of interior nonelastomeric shim members,
providing a plurality of interior erastomeric shim members,
providing a first metal first: laminate end structural bond shim,
providing a second metal distal end member,
disposing said interior nonelastorneric shim members, said interior elastomeric
shim members, said first metal first tarninate end structural bond shim, and said second
metal distal end member in said elastorneric subassembly bonding mold with said
interior nonelastomeric shim members and said interior elastomeric shim members
alternating and sandwiched between said first metal first laminate end structural bond
shim and said second metal distal end member,
mold bonding said interior nonelastomeric shim members, said interior
elastomeric shim members, said first metal first laminate end structural bond shim and
said second metal distal end member together in said elastomeric subassembly
bonding mold to provide an elastomeric mold bonded laminated subassembly with said
alternating layers of interior nonelastomeric shim members and interior elastorneric
shim members sandwiched between said first metal first laminate end structural bond
shim and said second metal distal end member, said elastorneric mold bonded
laminated subassembly having an elastomeric subassembly tensile strength ESTS
between said first metal first laminate end structural bond shim and said second metal
distal end member,
providing a post-elastomeric mold bond structural chemical adhesive,
providing a first end bearing connector first: metal member,
borrding,said first end bearing connector first metal member and said first metal
first laminate end structural bond shim with said post-elastorneric mold bond structural
chemical adhesive to provide a first end structural bond having an elongation of at least
1 A %, and a first end tensile strength FETS with FETS 2 ESTS.
23. A method of making a rotary wing aircraft bearing as claimed in claim 22, wherein
providing a plurality of interior nonelastomeric shim members, providing a first metal first
laminate end structural bond shim, includes providing a plurality of spherical shell
segment interior nonelastomeric shim members, providing a first spherical shell
segment metal first laminate end structural bond shim.
24. A method of making a rotary wing aircraft bearing as claimed in claim 23 including
maintaining a post-elastomeric mold bond structural chemical adhesive bond thickness
between said first end bearing connector first metal member and said first metal first
laminate end structural bond shim during an adhesive bond cure time to provide a first
spherical shell segment bond.
25. A method as claimed in claim 22 wherein said first end bearing connector first metal
member and said first metal first laminate end structural bond shim are comprised of a
first metal composition.
26. A method as claimed in claim 22 including maintaining a post-elastomeric mold
bond structural chemical adhesive bond thickness between said first end bearing
connector first metal member and said first metal first laminate end structural bond shim
during an adhesive bond cure time to provide a first end post-elastomeric mold bond
structural chemical adhesive bond thickness.
27. A method as claimed in claim 26, including a providing a fixturing jig, disposing said
rotary wing aircraft bearing in said fixturing jig during said adhesive bond cure time.
28. A nretb.wl, as - clai~~se.idn.- .c laim 42,. w;he-i~ ein....saifdir s+ end,.s tructu.ral%-r:kemical
adhesive post-elastomeric mold bond is comprised of a spherical shell segment. ,
29. A method as claimed in claim 22, wherein said first end structural chemical
adhesive post-elastomeric mold bond is tubular,
30. A method as claimed in claim 29, said first end structural chemical adhesive postelastomeric
mold bond is comprised of a conical shell segment.
31. A method as claimed in claim 22, wherein said second metal distal end member is
comprised of a tube.
32. A method as claimed in claim 31 wherein said distal second end interior
nonelastomeric shim member has a shim thickness Tinteiiarshim, and said second metal
distal end member tube has a tube thickness with Ttube> 5 Tintaiiorshim,
33. A method as claimed in claim 31 wherein said first metal first laminate end
structural bond shim has a shim thickness Texieriorshim with Ttube > 5 Textericwhirn.
34. A method as ciaimed in claim 22 wherein said interior nonelastomeric shim
members have a shim thickness Tiideriorshim, and said first metal first laminate end
structural bond shim has a shim thickness TexterioFswhitlmh T efieriorshimz Tinteriowhim.
Dated this 2oth day of June 2012.