Abstract:
Motion control bearings and methods making such with the capability to monitor properties therein is provided. Devices and methods for creating and using motion control bearings for rotary wing aircraft in particular are disclosed using wireless communication and monitoring of multiple load, motion and health related information items related to the bearing and blade at the wing hub. Static and dynamic blade orientation provides additional information on flight regime, thrust vectors, and gross vehicle weight. Power is provided using kinetic energy power harvesting.

Description:
BACKGROUND 
       [0001]    The invention relates generally to motion control bearings and methods of making motion control bearings for monitoring of properties therein. The invention relates to rotary wing aircraft and motion control bearings. The invention relates to motion control bearings in helicopter rotary wing systems. 
         [0002]    Motion control bearings are configured to be attached between two controlled member structures in order to control relative motion between the two structures. The motion control bearings preferably include at least one elastomer laminate bonded to two distal surfaces subjected to relative motion. The motion control bearings control a motion. 
       SUMMARY 
       [0003]    In one aspect the invention includes a bearing device for a rotary wing aircraft. The bearing device provides a constrained relative motion between a first control member and a second control member. The bearing device comprises an elastomeric laminate, a first end bearing connector, a second end bearing connector and at least a first sensor member. The elastomeric laminate including a plurality of mold bonded alternating layers of nonelastomeric shims and elastomeric shims. The first end bearing connector bonded with a first end of the elastomeric laminate. The first end bearing connector for grounding with the first control member. The second end bearing connector bonded with a second distal end of the elastomeric laminate. The second end bearing connector for grounding with the second control member. The first sensor member coupled with the first end bearing connector, a wireless transmitter, and a kinetic energy power harvester. The kinetic energy power harvester is disposed proximate to the elastomeric laminate, wherein the kinetic energy power harvester extracts an electrical energy from a energy source to provide electricity to the bearing device, wherein the first sensor member senses a movement between the first end bearing connector and the second end bearing connector, and the wireless transmitter transmits sensor data of the sensed movement to a wireless receiver. 
         [0004]    In one aspect, the invention includes a method of making a motion control bearing device for a rotary wing aircraft. The method of making the bearing device includes constraining a relative motion between a first control member and a second control member. The method comprises providing an elastomeric laminate, at least a first sensor member, a wireless transmitter, and a kinetic energy power harvester. The elastomeric laminate includes a plurality of mold bonded alternating layers of nonelastomeric shims and elastomeric shims. The elastomeric laminate includes a first end bearing connector bonded with a first end of the elastomeric laminate. The elastomeric laminate includes a second end bearing connector bonded with a second distal end of the elastomeric laminate. The kinetic energy power harvester extracts an electrical energy from a energy source to provide electricity to the bearing device, wherein the first sensor member senses a movement between the first end bearing connector and the second end bearing connector, and the wireless transmitter transmits sensor data of the sensed movement to a wireless receiver. 
         [0005]    In another aspect, the invention includes a bearing device. The bearing device provides a constrained relative motion between a first control member and a second control member. The bearing device comprises an elastomeric laminate  16  and a sensing means. The elastomeric laminate includes a plurality of mold bonded alternating layers of nonelastomeric shims and elastomeric shims. The bearing device includes a first end bearing connector bonded with a first end of the elastomeric laminate, the first end bearing connector for grounding with the first control member. The bearing device including a second end bearing connector bonded with a second distal end of elastomeric laminate, the second end bearing connector for grounding with the second control member. The sensing means has a means for powering the sensing means, wherein the sensing means senses a movement between the first end bearing connector and the second end bearing connector, and transmits sensor data of the sensed movement to a wireless receiver. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0006]      FIG. 1  illustrates a side view of a rotary wing aircraft. 
           [0007]      FIG. 2  illustrates detailed cross-section of motion control bearing location on rotary wing aircraft with wireless communications. 
           [0008]      FIG. 3  illustrates a schematic of a motion control bearing positioned about the center hub of a rotary wing aircraft. 
           [0009]      FIG. 4  illustrates a schematic of a motion control bearing. 
           [0010]      FIG. 5  illustrates a flow diagram of a wireless sensor for a motion control bearing. 
           [0011]      FIGS. 6-9  illustrate placement of sensors in an elastomeric device. 
           [0012]      FIG. 10  illustrates a schematic of the CF bearing and the placement thereof in the hub configuration. 
           [0013]      FIG. 11  illustrates wired communication through the fixed member of the CF bearing. 
           [0014]      FIG. 12  illustrates the attachment of the bonded spherical elastomeric bearing package to major metal components. 
           [0015]      FIG. 13  illustrates a section view of a bonded spherical elastomeric bearing with major metal components. 
           [0016]      FIG. 14  illustrates positioning bonded spherical elastomeric bearing package in a mold. 
           [0017]      FIG. 15  illustrates an exploded view of a rotary wing hub with the motion control bearing instrumented for load sensing. 
           [0018]      FIGS. 16 and 17  illustrate a sectional view of the motion control bearing in a portion of a rotary wing hub. 
           [0019]      FIG. 18  illustrates the kinetic energy power harvester. 
           [0020]      FIGS. 19 and 20  illustrate an exploded view of the kinetic energy power harvester without an elastomeric element. 
           [0021]      FIG. 21  illustrates a bottom view of the kinetic energy power harvester without an elastomeric element, including the winding and plurality of magnets. 
           [0022]      FIG. 22  illustrates a sectional side view of the kinetic energy power harvester without the elastomeric element, including the winding. 
           [0023]      FIG. 23  illustrates a perspective sectional side view of the kinetic energy power harvester without the elastomeric element, including the plurality of magnets. 
           [0024]      FIG. 24  illustrates a perspective side view of the load sensing assembly. 
           [0025]      FIG. 25  illustrates a control circuit for the load sensing assembly. 
           [0026]      FIG. 26  illustrates a perspective exploded view of the load sensing assembly. 
           [0027]      FIG. 27  illustrates the magnetic field associated with the motion control bearing. 
           [0028]      FIG. 28  illustrates a longitudinally extending linear displacement sensor assembly. 
           [0029]      FIG. 29  illustrates a schematic placement of multiple sensors. 
           [0030]      FIG. 30  illustrates a schematic placement of multiple sensors. 
       
    
    
     DETAILED DESCRIPTION 
       [0031]    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 skilled in the art from that description or recognized by practicing the invention as described herein, including the detailed description which follows, the claims, as well as the appended drawings. Reference will now be made in detail to the present preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. 
         [0032]    In an embodiment, the invention includes a rotary wing aircraft motion control bearing device  10 , hereinafter bearing device  10 . The bearing device  10  provides a constrained relative motion between a first rotary wing aircraft control member  12  and a second rotary wing aircraft control member  14 , hereinafter first control member  12  and second control member  14 . The bearing device  10  includes an elastomeric mold bonded laminate  16 . The elastomeric mold bonded laminate  16 , is hereinafter referred to as elastomeric laminate  16 . Although illustrated in  FIGS. 3 and 4  as a spherical elastomeric laminate  16 , elastomeric laminate  16  may be also be cylindrical. 
         [0033]    The elastomeric laminate  16 , including a plurality of mold bonded alternating layers of interiorly positioned nonelastomeric shims  18  and elastomeric shims  20 , preferably vulcanized bonded inside an elastomeric curing mold  22  which contains and positions the shims  18 ,  20  during an applied mold pressure and temperature to provide elastomeric laminate  16  of cured elastomer shims  20  and nonelastomeric shims  18 . The plurality of mold bonded alternating layers make up the bonded spherical elastomeric bearing package of elastomeric laminate  16 . 
         [0034]    The bearing device  10  includes a first end bearing connector  24  bonded with a first end  26  of the elastomeric laminate  16 , the first end bearing connector  24  for grounding with the first controlled member  12 , the bearing device  10  including a second end bearing connector  28  nonelastomeric metal member bonded with a second distal end  32  of the elastomeric laminate  16 , the bearing device  10  second end bearing connector  28  for grounding with the second control member  14 . 
         [0035]    The bearing device  10  includes at least a first sensor member  34 , the first sensor member  34  coupled with the first end bearing connector  24 . The bearing device  10  includes a sensor data wireless transceiver transmitter  36  and a kinetic energy ambient environmental power harvester  38 , hereinafter a kinetic energy power harvester  38 . The sensor data wireless transceiver transmitter  36  is hereinafter referred to as the wireless transmitter  36 . Wireless transmitter  36  is any type of wireless transmitter that is adaptable to bearing device  10  and able to electronically communicate. 
         [0036]    The kinetic energy power harvester  38  is disposed proximate the elastomeric laminate  16  wherein the kinetic energy power harvester  38  extracts an electrical energy from a energy source  40  associated with the rotary wing aircraft  42  to provide electrical energy in the form of electricity to the bearing device  10 . Preferably, the relative motion between the first control member  12  and the second control member  14  drives the kinetic energy power harvester  38 . The kinetic energy power harvester  38  provides electricity wherein the first sensor member  34  senses a movement between the first end bearing connector  24  and a second end bearing connector  28 , and the wireless transmitter  36  transmits sensor data of the sensed movement to a data wireless transceiver receiver  44  and associated electronics  45 . The data wireless transceiver receiver  44  is hereinafter referred to as the wireless receiver  44 . Alternatively, first sensor member  34  is in electrical communication with the rotary wing aircraft  42  power supply (not shown) receives supplemental power therefrom on an as required basis. 
         [0037]    Preferably, the elastomeric laminate  16  is comprised of a spherical shell segment  46  including a plurality of mold bonded alternating spherical segment shell layers of increasing/decreasing radius of nonelastomeric spherical segment shell layer shims  48  and elastomeric spherical segment shell layer shims  50 , the first end bearing connector  24  having a spherical shell segment  46  bonded with the first end  26  of the elastomeric laminate  16 , the bearing device  10  first end bearing connector  24  for grounding with the first control member  12 , the bearing device  10  second distal end bearing connector  28  having a spherical shell segment  46  bonded with the second distal end  32  of the elastomeric laminate  16 . Preferably the bearing device  10  is a replaceable limited use device in the rotary wing aircraft, preferably with the aircraft bearing device exchanged out for a replacement part that replaces the used bearing device. 
         [0038]    Preferably, the bearing device  10  includes a second sensor member  52 , the second sensor member  52  coupled with the first end bearing connector  24 . In a preferred embodiment the first and second sensor members  34 ,  52  oriented and coupled on the bearing device  10  are oriented accelerometers, with the accelerometers oriented relative to the rotary wing hub axis of rotation  54 . Preferably the accelerometers oriented relative to the rotary wing hub axis of rotation  54  and opposite to each other with the longitudinally extending blade axis  56  between and with the accelerometers oriented relative to the bearing center of rotation  58 , preferably with the opposing accelerometers providing rotational accelerometer data from rotation about the rotary wing hub axis of rotation  54  to provide position measurement data from the sensed rotational acceleration. 
         [0039]    Preferably, the bearing device  10  first sensor member  34  is comprised of a longitudinally extending sensor  60  extending along a longitudinal sensor axis  62  from a first sensor end  64  to a distal second end  66 . Preferably, the longitudinally extending sensor  60  distal second end  66  is coupled with the second end bearing connector  28 . In a preferred embodiment the longitudinally extending sensor  60  is a linear variable differential transformer. In an embodiment, the longitudinally extending sensor  60  detects a targeted detected section of the second end bearing connector  28 , preferably with the longitudinally extending sensor  60  comprised of a non-contact variable differential transformer  70 . The longitudinally extending sensor  60  distal second end  66  is coupled with the second end bearing connector  28  and is preferably a complementing sensor member pair end  72  to the first sensor member  34  first sensor end  64 . The complementing sensor member pair ends  72  sensing a position characteristic between the first end bearing connector  24  and the second end bearing connector  28  along a longitudinally extending axis  74 . The longitudinal sensor axis  62  is aligned with the longitudinally extending axis  74 , a longitudinally extending linear displacement sensor assembly  78 , a longitudinally extending variable reluctance transducer sensor assembly, and a longitudinally extending differential variable reluctance transducer sensor assembly. Preferably, the longitudinally extending sensor  60  is comprised of a longitudinally extending linear displacement sensor assembly  78 . In embodiments the longitudinally extending sensor  60  is a displacement transducer, preferably with axial displacement between conductive surfaces changes the space between the conductive surfaces with a sensed electrical change providing sensor data relative to the displacement between the end bearing connector  24 ,  28 . 
         [0040]    In a preferred embodiment the longitudinally extending linear displacement sensor assembly  78  includes an elongating electrical conductor, preferably a longitudinally extending contained elongating electrical conductor fluid  88  with a change in electrical characteristic relative to elongation. In a preferred embodiment, resistance of the electrical conductor changes with the changing displacement. In a preferred embodiment, the electrical conductor is a liquid metal mass, preferably a liquid metal mass comprised of Gallium and Indium. 
         [0041]    In preferred embodiments, the bearing device  10  includes a plurality of complementing pair longitudinally extending sensor member assemblies  90  sensing position characteristics between the first end bearing connector  24  and the second end bearing connector  28 , preferably with their longitudinally extending sensor  60  having nonparallel axes. Preferably the longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 , preferably with nonparallel axis  92  oriented nonparallel to the bearing center z axis  94 . Preferably four longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 , preferably with their longitudinally extending axis  74  nonparallel to each other and oriented relative to the rotary wing hub axis of rotation  54 . 
         [0042]    The bearing device  10  includes a load sensing assembly  96 , the load sensing assembly  96  powered with the kinetic energy power harvester  38  with the load sensing assembly  96  transmitting load sensor data through the wireless transmitter  36  to the wireless receiver  44 . Preferably the load sensing assembly  96  is comprised of a plurality of strain gauge bridges coupled with the first end bearing connector  24 . 
         [0043]    Preferably, the kinetic energy power harvester  38  includes a winding  102  and a plurality of magnets  104 . Preferably, the kinetic energy power harvester  38  is an ambient kinetic energy power harvester  38  including a winding  102  and a plurality of magnets  104 . 
         [0044]    Preferably, the bearing device  10  includes a second elastomeric mold bonded laminate  106 , hereinafter referred to as the second elastomeric laminate  106 . The second elastomeric laminate  106  including a plurality of second elastomeric laminate  106  mold bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 , preferably vulcanized bonded inside an elastomeric curing mold  112  which contains and positions the shims  108 ,  110  during an applied mold pressure and temperature to provide second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . Preferably the kinetic energy power harvester  38  is coupled with the second elastomeric laminate  106 . The second elastomeric laminate  106  is a cylindrical elastomeric laminate with mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , circular flat planar shims providing the cylindrical mold bonded laminate  114 , and with the second elastomeric laminate  106  comprising a cylindrical mold bonded laminate pitch bearing. Cylindrical mold bonded laminate  114  is second elastomeric laminate  106  in cylindrical form. 
         [0045]    Preferably, the bearing device  10  second elastomeric laminate  106  includes a plurality of second elastomeric laminate  106  mold bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 , preferably vulcanized bonded inside an elastomeric curing mold  112  which contains and positions the shims  108 ,  110  during an applied mold pressure and temperature to provide second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . The bearing device  10  second cylindrical second elastomeric laminate  106  is coupled with the kinetic energy power harvester  38  which includes a winding  102  and a plurality of magnets  104 . The bearing device  10  second cylindrical second elastomeric laminate  106  coupled with the kinetic energy power harvester  38  provides electrical power from the controlled cyclical pitching motion of the rotor wing. Preferably, the second elastomeric laminate  106  includes mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , circular flat planar shims  108 ,  110  provide cylindrical mold bonded laminate pitch bearing. 
         [0046]    Preferably, the bearing device  10  includes a second sensor member  52 , the second sensor member  52  coupled with the second end bearing connector  28 . In preferred embodiments the bearing device  10  includes a first magnetic field sensing first sensor member  118 , preferably a magnetometer  118 , and the second sensor member  52  is comprised of a second magnetic sensor target  120  coupled with the second end bearing connector  28 . Preferably the magnetometer is a three axis magnetometer, oriented and centered on the first end bearing connector  24  longitudinally extending axis  74 . The three axis magnetometer is comprised of three orthogonal vector magnetometers measuring magnetic field components including magnetic field strength, inclination and declination. 
         [0047]    The second oriented magnetic sensor target  120  is coupled with the second end bearing connector  28 . The permanent magnet target  122  is oriented and centered on the second end bearing connector  28  longitudinally extending axis  74 , with the permanent magnet target  122  generating magnetic field lines  123 . In an embodiment, the second end bearing connector  28  is comprised of a nonmagnetic metal, the first end bearing connector  24  is comprised of a nonmagnetic metal, and the interior nonelastomeric shims  18  are comprised of a nonmagnetic metal. 
         [0048]    In an embodiment, the second end bearing connector  28  is comprised of a magnetic metal. In an embodiment, the first end bearing connector  24  is comprised of a magnetic metal. In an embodiment at least one of the nonelastomeric shims  18  are comprised of a magnetic metal. Preferably with the oriented magnetometer and the distal permanent magnet target  122 , the relative location of the sensor within the magnet&#39;s magnetic field is measured. The magnetometer readings from the three axes is filtered and processed to produce signals which are proportional to the x, y, z axis displacement between the magnet and sensor. Preferably the magnetometer is oriented and centered on the central axis  124  of the spherical bearing  126 , the magnetometer&#39;s three axes are oriented in relation to the magnetic field lines  123  of the permanent magnet target  122 . 
         [0049]    The bearing device  10  has an operational lifetime beginning spring rate SRB and an operational lifetime end spring rate SRE with SRE&lt;SRB. Preferably, the SRE is no greater than 0.83SRB, preferably no greater than 0.81SRB, and preferably the operational lifetime end spring rate is less than eighty percent of operational lifetime beginning spring rate. The bearing device  10  has an operational lifetime OL measured by a plurality of operational deflection cycles between the first end bearing connector  24  and the second end bearing connector  28  until the operational lifetime end spring rate SRE is reached. Wherein, the bearing device  10  has the operational lifetime OL with the at least first magnetic field sensing first sensor member  118  monitoring an operational spring rate of the elastomeric laminate  16  between the first end bearing connector  24  and the second end bearing connector  28 . The device monitors the operational spring rate of the elastomeric laminate  16  relative to the SRB and the SRE. 
         [0050]    Preferably, the wireless transmitter  36  transmits sensor data to the wireless receiver  44  with the sensor data including operational spring rate data of the elastomeric laminate  16 . The sensor data is used to determine replacement of the bearing device  10 . The sensor data is used to monitor bearing device  10  usage, monitor and collect loading history statistics experienced by the bearing, catalog usage exceedance events (bearing events that relate to bearing stress and/or strain that exceeds predefined threshold indicating significant damage, compromised bearing life, need for near-term inspection or removal/replacement, estimate remaining bearing life, monitor loading history for tracking cumulative damage). Preferably, the rotary wing aircraft constrained relative motion operational deflection cycles compress the elastomers of the elastomeric laminate  16 , compressing and/or shearing the intermediate elastomer. 
         [0051]    Preferably, the sensors monitor operational lifetime OL cycles of at least about forty five million cycles to about eighty nine million cycles. Preferably, the sensors monitor operational lifetime OL cycles for at least about 2,450 hours at about 5 HZ to at least about 4,000 hours at about 6 Hz. The operational lifetime OL cycles, hours and frequency ranges are platform dependent and vary based upon the particular design requirements for the rotary wing aircraft  42 . Preferably the spring rate cycle sensor data is used to initiate a replacement of the bearing device  10  in the aircraft, with the bearing device  10  comprised of a replaceable limited use device, preferably with the device exchanged out for a replacement part. 
         [0052]      FIG. 2  illustrates the placement of bearing device  10  on rotary wing aircraft  42  near rotary wing hub  125  near blade root  127   a  and  127   b.    
         [0053]    In an embodiment, elastomeric laminate  16 , spherical shell segment  46 , and bonded spherical elastomeric package each refer to elastomer layers and shims bonded together. There are two approaches to make these parts. The first approach is by bonding nonelastomeric shims  18 ,  48  and elastomeric shims  20 ,  50  in a mold  22 . The bonded shim package is then attached to first end bearing connector  24  and second end bearing connector  28 . The second approach is by bonding nonelastomeric  18 ,  48  and elastomeric shims  20 ,  50  in a mold  22  together with first end bearing connector  24  and second end bearing connector  28 . 
         [0054]    In an embodiment, the invention includes a method of making a bearing device  10  for providing a constrained relative motion between a first control member  12  and a second control member  14 . The method includes providing an elastomeric laminate  16 , the elastomeric laminate  16  including a plurality of mold bonded alternating layers of nonelastomeric shims  18  and elastomeric shims  20 . Preferably, the elastomeric laminate  16  is provided by vulcanize bonding inside an elastomeric curing mold  22  which contains and positions the shims  18 ,  20  during an applied mold pressure and temperature to provide the elastomeric laminate  16  of cured elastomer shims  20  and nonelastomeric shims  18 . The plurality of mold bonded alternating layers make up the bonded spherical elastomeric bearing package of elastomeric laminate  16 . The elastomeric laminate  16  preferably includes a first end bearing connector  24  bonded with a first end  26  of the elastomeric laminate  16 . The bearing device  10  first end bearing connector  24  is for grounding with the first control member  12 . 
         [0055]    The elastomeric laminate  16  preferably includes a second end bearing connector  28  bonded with a second distal end  32  of the elastomeric laminate  16 , the bearing device  10  second end bearing connector  28  for grounding with the second control member  14 . The method includes providing at least a first sensor member  34 , the first sensor member  34  coupled with the first end bearing connector  24 , a wireless transmitter  36 , and a kinetic energy power harvester  38 . The kinetic energy power harvester  38  is disposed proximate the elastomeric laminate  16 , wherein the kinetic energy power harvester  38  extracts an electrical energy flow from a energy source  40  to provide electricity. Preferably, energy source  40  is a kinetic energy source. Wherein the first sensor member  34  senses a movement between the first end bearing connector  24  and the second end bearing connector  28 , and the wireless transmitter  36  transmits sensor data of the sensed movement to a wireless receiver  44 . 
         [0056]    Preferably, the elastomeric laminate  16  is comprised of a spherical shell segment  46  including a plurality of mold bonded alternating spherical segment shell layers of increasing/decreasing radius of nonelastomeric spherical segment shell layer shims  48  and elastomeric spherical segment shell layer shims  50 . The first end bearing connector  24  has a spherical shell segment  46  bonded with the first end  26  of the elastomeric laminate  16 . The bearing device  10  first end bearing connector  24  for grounding with the first control member  12 , the bearing device  10  second end bearing connector  28  having a spherical shell segment  46  bonded with the second distal end  32  of the elastomeric laminate  16 . 
         [0057]    Preferably, the method includes providing a second sensor member  52 , the second sensor member  52  coupled with the first end bearing connector  24 . In preferred methods, the first and second sensors  34 ,  52  are accelerometers oriented relative to the rotary wing hub axis of rotation  54 , with the coupled position of the accelerometer measured with rotational acceleration. 
         [0058]    Preferably, the method includes the first sensor member  34  comprised of a longitudinally extending sensor  60  extending along a longitudinal sensor axis  62  from a first sensor end  64  to a distal second end  66 . The longitudinally extending sensor  60  distal second end  66  is coupled with the second end bearing connector  28 . 
         [0059]    In an embodiment, the longitudinally extending sensor  60  distal second end  66  coupled with the second end bearing connector  28  is the second end bearing connector  28 . In an embodiment, the longitudinally extending sensor  60  is a linear variable differential transformer. In an embodiment, the longitudinally extending sensor  60  is a non-contact variable differential transformer sensing a targeted detected section of the second end bearing connector  28 . 
         [0060]    Preferably, the longitudinally extending sensor  60  distal second end  66  coupled with the second end bearing connector  28  is preferably a complementing sensor member pair end  72  to the first sensor member  34  first sensor end  64 , with the complementing sensor member pair ends  72  sensing a position characteristic between the first end bearing connector  24  and the second end bearing connector  28  preferably along a longitudinally extending axis  74  with the longitudinal sensor axis  62  aligned with the longitudinally extending axis  74 . The sensor assembly comprises a longitudinally extending linear displacement sensor assembly  78 , a longitudinally extending variable reluctance transducer sensor assembly, and a longitudinally extending differential variable reluctance transducer sensor assembly. 
         [0061]    In embodiments, the sensor is a displacement transducer, preferably with axial displacement between conductive surfaces changes the space between the conductive surfaces with a sensed electrical change providing sensor data relative to the displacement between the end bearing connector  24 ,  28 . 
         [0062]    In embodiments, the sensor is a longitudinally extending linear displacement sensor assembly  78 , preferably an elongating electrical conductor, preferably a longitudinally extending contained elongating electrical conductor fluid  88  with a change in electrical characteristic relative to elongation. Preferably, sensed change is resistance provides a sensed change in displacement. In embodiments, the longitudinally extending contained elongating electrical conductor fluid  88  is a liquid metal mass, and preferably a liquid metal mass comprised of Gallium and Indium. 
         [0063]    Preferably, the method includes disposing a plurality of the complementing pair longitudinally extending sensor member assemblies  90  sensing position characteristics between the first end bearing connector  24  and the second end bearing connector  28 , preferably with their longitudinally extending axis  74  nonparallel. The longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 . Preferably, four longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 , preferably with their longitudinally extending axis  74  nonparallel to each other and oriented relative to relative to the rotary wing hub axis of rotation  54 . 
         [0064]    Preferably, the method includes providing a load sensing assembly  96 , the load sensing assembly  96  powered with the kinetic energy power harvester  38  with the load sensing assembly  96  transmitting load sensor data through the wireless transmitter  36  to the wireless receiver  44 . Preferably, the load sensing assembly  96  is comprised of a plurality of strain gauge bridges coupled with the first end bearing connector  24 . 
         [0065]    Preferably, the method includes providing a kinetic energy power harvester  38  with a winding  102  and a plurality of magnets  104 . Preferably the kinetic energy power harvester  38  includes a winding  102  and a plurality of magnets  104  centered and coupled about a second elastomeric laminate  106  with controlled rotary wing cyclical motions. 
         [0066]    Preferably, the method includes providing a second elastomeric laminate  106 , the second elastomeric laminate  106  including a plurality of second elastomeric mold bonded laminate mold bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 . The method includes vulcanize bonding inside an elastomeric curing mold  112  which contains and positions the shims during an applied mold pressure and temperature to provide the second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . Preferably the kinetic energy power harvester  38  is coupled with the second elastomeric laminate  106 . The second elastomeric laminate  106  is mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , preferably circular flat planar shims providing a cylindrical mold bonded laminate, preferably cylindrical mold bonded laminate pitch bearing for controlling rotary wing cyclical motions. 
         [0067]    Preferably, the method includes providing a second elastomeric laminate  106 , the second elastomeric laminate  106  including a plurality of second elastomeric mold bonded laminate mold bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 , preferably vulcanize bonding inside an elastomeric curing mold  112  which contains and positions the shims during an applied mold pressure and temperature to provide second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . Preferably, the kinetic energy power harvester  38  includes a winding  102  and a plurality of magnets  104 , with the kinetic energy power harvester  38  coupled with the second elastomeric laminate  106 . Preferably, the second elastomeric laminate  106  is comprised of mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , preferably circular flat planar shims to provide cylindrical mold bonded laminate  114 , preferably a cylindrical mold bonded laminate pitch bearing. Cylindrical mold bonded laminate  114  is second elastomeric laminate  106  in cylindrical form. 
         [0068]    Preferably, the method includes providing a second sensor member  52 , the second sensor member  52  coupled with the second end bearing connector nonelastomeric  28 . Preferably, the second sensor member  52  coupled with the second end bearing connector  28  is a magnet. In preferred embodiments, the bearing device  10  is provided with a first magnetic field sensing first sensor member  34 , preferably a magnetometer, and the second sensor member  52  is comprised of a second magnetic sensor target  120  coupled with the second end bearing connector  28 . Preferably, the provided magnetometer is a three axis magnetometer, oriented and centered on the first end bearing connector  24  longitudinally extending center axis  74 . The three axis magnetometer is comprised of three orthogonal vector magnetometers measuring magnetic field components including magnetic field strength, inclination and declination. The second magnetic sensor target  120  is coupled with the second end bearing connector  28 , and the permanent magnet target  122  is oriented and centered on the second end bearing connector  28  longitudinally extending axis  74 , with the permanent magnet target  122  generating magnetic field lines  123 . 
         [0069]    In an embodiment the second end bearing connector  28  is comprised of a nonmagnetic metal; the first end bearing connector  24  is comprised of a nonmagnetic metal; and the nonelastomeric shims  18  are comprised of a nonmagnetic metal. In an embodiment, the second end bearing connector  28  is comprised of a magnetic metal. In an embodiment, the first end bearing connector  24  is comprised of a magnetic metal. In an embodiment, at least one of the nonelastomeric shims  18  are comprised of a magnetic metal. Preferably, with the magnetometer sensors and the distal permanent magnet targets, the relative location of the sensor within the magnet&#39;s magnetic field is measured. Preferably the magnetometer readings from the three axes is filtered and processed to produce signals which are proportional to the x, y, z axis displacement between the magnet and sensor. Preferably the magnetometer sensor is oriented and centered on the central axis of the spherical bearing, the sensor&#39;s three axes are oriented in relation to the magnetic field lines  123  of the permanent magnet target  122 . 
         [0070]    The bearing device  10  has an operational lifetime beginning spring rate SRB and an operational lifetime end spring rate SRE with SRE&lt;SRB. Preferably, the bearing device  10  has an operational lifetime beginning spring rate SRB and an operational lifetime end spring rate SRE with SRE&lt;SRB. Preferably, the SRE is no greater than 0.83SRB, preferably no greater than 0.81SRB, and preferably the operational lifetime end spring rate is less than eighty percent of operational lifetime beginning spring rate. Preferably, the bearing device  10  has an operational lifetime OL measured by a plurality of operational deflection cycles between the first end bearing connector nonelastomeric metal member  24  and the second end bearing connector  28  until the operational lifetime end spring rate SRE is reached, wherein the bearing device  10  has the operational lifetime OL with the at least first sensor member  34  monitoring an operational spring rate of the elastomeric laminate  16  between the first end bearing connector nonelastomeric metal member  24  and the second end bearing connector  28 . 
         [0071]    Preferably, the bearing device  10  monitors the operational spring rate of the elastomeric laminate  16  relative to the SRB and the SRE. Preferably, the wireless transmitter  36  transmits sensor data to the wireless receiver  44  with the sensor data including operational spring rate data of the elastomeric laminate  16 . Preferably, the sensor data is used to determine replacement of the bearing device  10 . Preferably the sensor data is used to monitor bearing usage, preferably monitor and collect loading history statistics experienced by the bearing, catalog usage exceedance events (bearing events that relate to bearing stress and/or strain that exceeds predefined threshold indicating significant damage, compromised bearing life, need for near-term inspection or removal/replacement, estimate remaining bearing life, monitor loading history for tracking cumulative damage). 
         [0072]    Preferably, the rotary wing aircraft constrained relative motion operational deflection cycles compress the elastomers of the elastomeric laminate  16 , preferably shearing the intermediate elastomer, preferably compressing and shearing the intermediate elastomer. Preferably, the sensors monitor operational lifetime OL cycles of at least about forty five million cycles to about eighty nine million cycles. Preferably, the sensors monitor operational lifetime OL cycles for at least about 2,450 hours at about 5 HZ to at least about 4,000 hours at about 6 Hz. The operational lifetime OL cycles, hours and frequency ranges are platform dependent and vary based upon the particular design requirements for the rotary wing aircraft  42 . Preferably, the spring rate cycle sensor data is used to initiate a replacement of the bearing device  10  in the aircraft, with the bearing device  10  comprised of a replaceable limited use device, preferably with the device exchanged out for a replacement part. 
         [0073]    The bearing device  10  preferably provides load sensing, and preferably provides prognostics data for the bearing device  10  and preferably provides load information for improved regime recognition and usage information of the aircraft. Preferably, the bearing device  10  provides load and motion sensing. Preferably, the load sensing resolves moments associated with blade flapping, lead-lag, and pitch or the rotary wing aircraft. Preferably, the sensors provide for measuring in-plane and centrifugal forces with the bearing measuring loads in six degrees-of-freedom. The bearing device  10  preferably provides comprehensive loads and motions data on the rotor head, including six degrees-of-freedom blade/hub load sensing related to helicopter usage, regime recognition and fatigue cycles. The bearing device  10  preferably provides three axes of dynamic motion measurement (pitch, lead/lag, and flap) with real-time stiffness monitoring of the bearing for assessing both bearing and blade health. The bearing device  10  preferably provides static and dynamic blade orientation for the aircraft including information on flight regime, thrust vectors, and gross vehicle weight. 
         [0074]    Preferably the bearing device&#39;s  10  power harvesting provides for powering wireless communication of data to the fixed frame of the aircraft. The bearing device  10  preferably includes Moment Sensors, preferably strain gauges coupled to the spherical bearing end bearing connector member  128  to provide measurements of pitch, lead/lag and flap moments, preferably with full bridge strain gauges. The bearing device  10  preferably includes Force Sensors, preferably sensors providing measurements of in-plane, vertical and centrifugal loads. The bearing device  10  preferably includes Inertial Sensors, preferably located proximate the bearing device electronics module  130  to provide measurement of inertial motion in the pitch, lead/lag and flap directions, preferably providing dynamic displacements in these degrees-of-freedom. Preferably, the bearing device&#39;s  10  kinetic energy power harvester  38  is coupled to the system within the hub arm and harvests kinetic energy associated with the harmonic motion of the assembly. Preferably, the bearing device&#39;s electronics module  130  includes six strain bridges and three inertial sensors feeding into a sensor conditioning circuit. Preferably, the signal inputs are buffered and transmitted wirelessly as data packets to a fixed system transceiver. Preferably the bearing device electronics module  130  includes power management for optimal usage of harvested power. 
         [0075]    The bearing device  10  provides sensing of health through in situ dynamic stiffness measurements. The bearing device  10  provides load measurements to provide fatigue loading cycle counts and regime recognition. The bearing device  10  provides blade static position to provide regime recognition (e.g., pull-up, bank, etc) and aircraft gross weight (e.g, blade coning angle). Preferably, blade static position is provided with the inertial sensors and strain gauges to calculating bearing dynamic stiffness. Preferably, blade static position is provided with an empirical model to inferring bearing static stiffness from dynamic stiffness. Preferably, blade static position is provided with calculations from the strain gauges and static stiffness. Preferably, the bearing device  10  with longitudinally extending sensors  60  measure bearing motion, and preferably the sensor data is used in combination with load sensing data, preferably from the strain gages, to provide in situ stiffness measurements. Preferably, the bearing device  10  with longitudinally extending sensors  60  in the spherical elastomeric laminate measure bearing flap angle to provide data related to rotor coning angle relating to aircraft gross weight. Preferably, the bearing device  10 , with longitudinally extending sensors  60  in the spherical elastomeric laminate, measures usage behavior and operating regime recognition pertaining to the machinery, in which they reside. Preferably, the bearing device  10  with longitudinally extending sensors  60  in the spherical elastomeric laminate measure the bearing lead-lag angle to provide data on the operating state of the helicopter. Preferably, the bearing device  10  with longitudinally extending sensors  60  in the spherical elastomeric laminate measure motions of the bearing, preferably angular-x (lead-lag), angular-y (flap), angular-z (pitch) and z-displacement (CF). 
         [0076]    In an embodiment, the invention includes a method of making a bearing device  10 . The method includes providing an elastomeric laminate  16 , the elastomeric laminate  16  including a plurality of mold bonded alternating layers of nonelastomeric shims  18  and elastomeric shims  20 . Preferably the elastomeric laminate  16  is provided by vulcanize bonding inside an elastomeric curing mold  22  which contains and positions the shims during an applied mold pressure and temperature to provide the elastomeric laminate  16  of cured elastomer shims  20  and bonded nonelastomeric shims  18 . The plurality of mold bonded alternating layers make up the bonded spherical elastomeric bearing package of elastomeric laminate  16 . The elastomeric laminate  16  includes a first end bearing connector  24  bonded with a first end  26  of the elastomeric laminate  16 . The first end bearing connector  24  is preferably for grounding with a first control member  12 . The elastomeric laminate  16  includes a second end bearing connector  28  bonded with a second distal end  32  of the elastomeric laminate  16 . The bearing device  10  second distal end  32  second end bearing connector  28  preferably for grounding with the second control member  14 . The method includes providing at least a first sensor member  34 , a wireless transmitter  36 , and a kinetic energy power harvester  38 . The kinetic energy power harvester  38  is preferably disposed proximate the elastomeric laminate  16  wherein the kinetic energy power harvester  38  extracts an electrical energy flow to provide electricity wherein the first sensor member  34  senses a movement between the first end bearing connector  24  and the second end bearing connector  28  and the wireless transmitter  36  transmits sensor data of the sensed movement to a wireless receiver  44 . 
         [0077]    Preferably, the first sensor member  34  is coupled with the first end bearing connector  24 . Preferably, the kinetic energy power harvester  38  is a kinetic energy power harvester  38 . Preferably, the elastomeric laminate  16  is comprised a spherical shell segment  46  including a plurality of mold bonded alternating spherical segment shell layers of increasing/decreasing radius of nonelastomeric spherical segment shell layer shims  48  and elastomeric spherical segment shell layer shims  50 , the first end bearing connector  24  having a spherical shell segment  46  bonded with the first end  26  of the elastomeric laminate  16 , the bearing device  10  first end bearing connector  24  for grounding with the first control member  12 , the bearing device  10  second distal end  32  second end bearing connector  28  having a spherical shell segment  46  bonded with the second distal end  32  of the elastomeric laminate  16 . 
         [0078]    Preferably, the method including providing a second sensor member  52 , the second sensor member  52  coupled with the first end bearing connector  24 , preferably with first and second oriented accelerometers oriented relative to an axis of rotation, preferably with positions measured with rotational acceleration. 
         [0079]    Preferably, the first sensor member  34  is comprised of a longitudinally extending sensor  60  extending along a longitudinal sensor axis  62  from a first sensor end  64  to a distal second end  66 . Preferably, the method includes the first sensor member  34  comprised of a longitudinally extending sensor  60  extending along a longitudinal sensor axis  62  from a first sensor end  64  to a distal second end  66 . Preferably, the longitudinally extending sensor  60  distal second end  66  is coupled with the second end bearing connector  28 . In an embodiment, the longitudinally extending sensor  60  distal second end  66  coupled with the second end bearing connector  28  is the second end bearing connector  28 . In an embodiment, the longitudinally extending sensor  60  is a linear variable differential transformer. In an embodiment, the sensor is a non-contact variable differential transformer sensing a targeted detected section of the second end bearing connector  28 . 
         [0080]    Preferably, the longitudinally extending sensor  60  distal second end  66  coupled with the second end bearing connector  28  is a complementing sensor member pair end  72  to the first sensor member  34  first sensor end  64 . The complementing sensor member pair ends  72  sensing a position characteristic between the first end bearing connector  24  and the second end bearing connector  28  preferably along a longitudinally extending axis  74  with the longitudinal sensor axis  62  aligned with the longitudinally extending axis  74 . Preferably, the sensor assembly comprises a longitudinally extending linear displacement sensor assembly  78 , preferably a longitudinally extending variable reluctance transducer sensor assembly, and preferably a longitudinally extending differential variable reluctance transducer sensor assembly. In embodiments, the longitudinally extending sensor  60  is a displacement transducer, preferably with axial displacement between conductive surfaces changes the space between the conductive surfaces with a sensed electrical change providing sensor data relative to the displacement between the end bearing connector  24 ,  28 . In embodiments, the sensor is a longitudinally extending linear displacement sensor assembly  78 , preferably an elongating electrical conductor, preferably a longitudinally extending contained elongating electrical conductor fluid  88  with a change in electrical characteristic relative to elongation. Preferably, resistance provides a sensed change in displacement. Preferably, the longitudinally extending contained elongating electrical conductor fluid  88  is a liquid metal mass, more preferably a liquid metal mass comprised of Gallium and Indium. 
         [0081]    Preferably, the method includes disposing a plurality of the complementing pair longitudinally extending sensor member assemblies  90  sensing position characteristics between the first end bearing connector  24  and the second end bearing connector  28 , with their longitudinally extending axis  74  nonparallel. Preferably, the longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 . Preferably, four longitudinally extending sensor member assemblies  90  extend through the spherical shell segments  46 , with their longitudinally extending axis  74  nonparallel to each other and oriented relative to the rotary wing hub axis of rotation  54 . 
         [0082]    Preferably, the method includes providing a load sensing assembly  96 , the load sensing assembly  96  powered with the kinetic energy power harvester  38  with the load sensing assembly  96  transmitting load sensor data through the wireless transmitter  36  to the wireless receiver  44 . Preferably, the load sensing assembly  96  is comprised of a plurality of strain gauge bridges coupled with the first end bearing connector  24 . 
         [0083]    Preferably, providing the kinetic energy ambient harvester  38  includes providing a kinetic energy power harvester  38  with a winding  102  and a plurality of magnets  104 . 
         [0084]    Preferably, the method includes providing a second elastomeric laminate  106 , the second elastomeric laminate  106  including a plurality of second elastomeric laminate  106  mold bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 . Preferably, the method includes vulcanize bonding inside an elastomeric curing mold  112  which contains and positions the shims during an applied mold pressure and temperature to provide the second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . Preferably, the kinetic energy power harvester  38  is coupled with the second elastomeric laminate  106 . Preferably, the second elastomeric laminate  106  is mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , preferably circular flat planar shims providing a cylindrical mold bonded laminate  114 , preferably cylindrical mold bonded laminate pitch bearing for controlling cyclical motions. 
         [0085]    Preferably, the method includes providing a second elastomeric laminate  106 , the second elastomeric laminate  106  including a plurality of second elastomeric mold bonded laminate mold  106  bonded alternating layers of interiorly positioned nonelastomeric shims  108  and elastomeric shims  110 , preferably vulcanize bonding inside an elastomeric curing mold  112  which contains and positions the shims during an applied mold pressure and temperature to provide second elastomeric laminate  106  of cured elastomer shims  110  and nonelastomeric shims  108 . Preferably, the kinetic energy power harvester  38  includes a winding  102  and a plurality of magnets  104 , with the kinetic energy power harvester  38  coupled with the second elastomeric laminate  106 . Preferably, the second elastomeric laminate  106  is comprised of mold bonded alternating layers of flat planar nonelastomeric shims  108  and flat planar elastomeric shims  110 , preferably circular flat planar shims to provide cylindrical mold bonded laminate  114 , preferably a cylindrical mold bonded laminate pitch bearing. 
         [0086]    Preferably, the method includes providing a second sensor member  52 , the second sensor member  52  coupled with the second end bearing connector  28 . Preferably, the second sensor member  52  coupled with the second end bearing connector  28  is a magnet. In preferred embodiments, the bearing device  10  is provided with a first magnetic field sensing first sensor member  118 , preferably a magnetometer, and the second sensor member  52  is comprised of a second magnetic sensor target  120  coupled with the second end bearing connector  28 . Preferably, the provided magnetometer is a three axis magnetometer, preferably oriented and centered on the first end bearing connector  24  longitudinally extending axis  74 . Preferably, the three axis magnetometer is comprised of three orthogonal vector magnetometers measuring magnetic field components including magnetic field strength, inclination and declination. 
         [0087]    Preferably, the second magnetic sensor target  120  is coupled with the second end bearing connector  28 , preferably the permanent magnet target  122  is oriented and centered on the second end bearing connector  28  longitudinally extending axis  74 , with the permanent magnet target  122  generating magnetic field lines  123 . In an embodiment, the second end bearing connector  28  is comprised of a nonmagnetic metal, the first end bearing connector  24  is comprised of a nonmagnetic metal, and the nonelastomeric shims  18  are comprised of a nonmagnetic metal. In an embodiment, the second end bearing connector  28  is comprised of a magnetic metal. In an embodiment, the first end bearing connector  24  is comprised of a magnetic metal. In an embodiment, at least one of the nonelastomeric shims  18  are comprised of a magnetic metal. Preferably, with the magnetometer sensor and the permanent magnet target  122 , the relative location of the second magnetic sensor target  120  within the magnet&#39;s magnetic field is measured. Preferably, the magnetometer readings from the three axes is filtered and processed to produce signals which are proportional to the x, y, z axis displacement between the magnet and sensor. Preferably, the magnetometer sensor is oriented and centered on the central axis of the spherical bearing. The sensor&#39;s three axes are oriented in relation to the magnetic field lines  123  of the permanent magnet target  122 . 
         [0088]    The method includes providing a bearing device  10  with an operational lifetime beginning spring rate SRB and an operational lifetime end spring rate SRE with SRE&lt;SRB. Preferably, the bearing device  10  has an operational lifetime beginning spring rate SRB and an operational lifetime end spring rate SRE with SRE&lt;SRB. Preferably, the SRE is no greater than 0.83SRB, preferably no greater than 0.81SRB, and preferably the operational lifetime end spring rate is less than eighty percent of operational lifetime beginning spring rate. Preferably, the bearing device  10  has an operational lifetime OL measured by a plurality of operational deflection cycles between the first end bearing connector  24  and the second end bearing connector  28  until the operational lifetime end spring rate SRE is reached. Wherein the bearing device  10  has the operational lifetime OL with the at least first sensor member  34  monitoring an operational spring rate of the elastomeric laminate  16  between the first end bearing connector nonelastomeric metal member  24  and the second end bearing member  28 . Preferably, the bearing device  10  monitors the operational spring rate of the elastomeric laminate  16  relative to the SRB and the SRE. Preferably, the wireless transmitter  36  transmits sensor data to the wireless receiver  44  with the sensor data including operational spring rate data of the elastomeric laminate  16 . Preferably, the sensor data is used to determine replacement of the bearing device  10 . Preferably, the sensor data is used to monitor bearing usage, preferably monitor and collect loading history statistics experienced by the bearing, catalog usage exceedance events (bearing events that relate to bearing stress and/or strain that exceeds predefined threshold indicating significant damage, compromised bearing life, need for near-term inspection or removal/replacement, estimate remaining bearing life, monitor loading history for tracking cumulative damage). Preferably, the constrained relative motion operational deflection cycles compress the elastomers of the elastomeric laminate  16 , preferably shearing the intermediate elastomer, preferably compressing and shearing the intermediate elastomer. 
         [0089]    Preferably, the sensors monitor operational lifetime OL cycles of at least about forty five million cycles to about eighty nine million cycles. Preferably, the sensors monitor operational lifetime OL cycles for at least about 2,450 hours at about 5 HZ to at least about 4,000 hours at about 6 Hz. The operational lifetime OL cycles, hours and frequency ranges are platform dependent and vary based upon the particular design requirements for the rotary wing aircraft  42 . Preferably the spring rate cycle sensor data is used to initiate a replacement of the bearing device  10 , with the bearing device  10  comprised of a replaceable limited use device, preferably with the device exchanged out for a replacement part. 
         [0090]    In an embodiment, the invention includes a bearing device  10 , the bearing device  10  providing a constrained relative motion between a first control member  12  and a second control member  14 . The bearing device  10  includes an elastomeric laminate  16 , the elastomeric laminate  16  including a plurality of mold bonded alternating layers of nonelastomeric shims  18  and elastomeric shims  20 . The elastomeric laminate  16  is preferably vulcanized bonded inside an elastomeric curing mold  22  which contains and positions the shims during an applied mold pressure and temperature to provide an elastomeric laminate  16  of cured elastomer shims  20  and nonelastomeric shims  18 . The bearing device  10  includes a first end bearing connector  24  bonded with a first end  26  of the elastomeric laminate  16 , the first end bearing connector  24  for grounding with the first control member  12 . The bearing device  10  including a second end bearing connector  28  bonded with a second distal end  32  of the elastomeric laminate  16 , the second end bearing connector  28  for grounding with the second control member  14 . The elastomeric laminate  16  can be attached to the first end bearing connector  24  and the second end bearing connector  28  after the elastomeric laminate  16  is cured in the elastomeric curing mold  22 . Sensor members  34 ,  52  may be attached after the elastomeric laminate  16  is cured in the elastomeric curing mold  22 . 
         [0091]    The bearing device  10  includes a means for sensing and a means for powering the sensing means, wherein the sensing means senses a movement between the first end bearing connector  24  and the second end bearing connector  28 , and transmits sensor data of the sensed movement to a wireless receiver  44 . Preferably, the elastomeric laminate  16  is comprised of a spherical shell segment  46  including a plurality of mold bonded alternating spherical segment shell layers of increasing/decreasing radius of interiorly positioned nonelastomeric spherical segment shell layer shims  48  and elastomeric spherical segment shell layer shims  50 , the first end bearing connector  24  having a spherical shell segment  46  bonded with the first end  26  of the elastomeric laminate  16 , the rotary wing aircraft bearing first end bearing connector  24  for grounding with the first control member  12 . The rotary wing aircraft bearing second end bearing connector  28  having a spherical shell segment  46  bonded with the second distal end  32  of the elastomeric laminate  16 . 
         [0092]    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).