公开(公告)号：US08336185B2

公开(公告)日：2012-12-25

申请号：US12974285

申请日：2010-12-21

Applicant: Frank O. James ,  Christopher F. Rajecki

Inventor： Frank O. James ,  Christopher F. Rajecki

IPC: B23P25/00

CPC classification number: F16F1/40 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59 ,  F16C7/04 ,  F16C11/0614 ,  F16C11/083 ,  F16F1/393 ,  Y10T29/49885 ,  Y10T29/4998 ,  Y10T29/49982 ,  Y10T403/47

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract translation: 本发明提供一种旋翼飞机直升机车辆杆端和制造杆端的方法。 旋转翼飞行器杆端包括具有外接合表面段和具有中心孔轴线的轴向孔的非弹性内部构件，具有内部接合表面区段和轴向孔中心孔轴线的非弹性外部构件，并且交替地模制就位 弹性垫片和非弹性垫片将非弹性内部构件连接到非弹性外部构件。 杆端包括结合到非弹性内部构件外部结合表面区段的第一内部弹性垫片和结合到非弹性外部构件内部结合表面区段和第二外部非弹性垫片的第一内部非弹性垫片和第二外部弹性垫片。 非弹性内部构件具有与外部非弹性外部构件的模制未对准旋翼机翼杆端部取向。

公开(公告)号：US20120134741A1

公开(公告)日：2012-05-31

申请号：US12974285

申请日：2010-12-21

Applicant: FRANK O. JAMES ,  Christopher F. Rajecki

Inventor： FRANK O. JAMES ,  Christopher F. Rajecki

IPC: B29C65/70 ,  B29C65/00

CPC classification number: F16F1/40 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59 ,  F16C7/04 ,  F16C11/0614 ,  F16C11/083 ,  F16F1/393 ,  Y10T29/49885 ,  Y10T29/4998 ,  Y10T29/49982 ,  Y10T403/47

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract translation: 本发明提供一种旋翼飞机直升机车辆杆端和制造杆端的方法。 旋转翼飞行器杆端包括具有外接合表面段和具有中心孔轴线的轴向孔的非弹性内部构件，具有内部接合表面区段和轴向孔中心孔轴线的非弹性外部构件，并且交替地模制就位 弹性垫片和非弹性垫片将非弹性内部构件连接到非弹性外部构件。 杆端包括结合到非弹性内部构件外部结合表面区段的第一内部弹性垫片和结合到非弹性外部构件内部结合表面区段和第二外部非弹性垫片的第一内部非弹性垫片和第二外部弹性垫片。 非弹性内部构件具有与外部非弹性外部构件的模制未对准旋翼机翼杆端部取向。

公开(公告)号：US20080247690A1

公开(公告)日：2008-10-09

申请号：US11861866

申请日：2007-09-26

Applicant: Frank O. James ,  Christopher F. Rajecki

Inventor： Frank O. James ,  Christopher F. Rajecki

IPC: F16C23/04

CPC classification number: F16F1/40 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59 ,  F16C7/04 ,  F16C11/0614 ,  F16C11/083 ,  F16F1/393 ,  Y10T29/49885 ,  Y10T29/4998 ,  Y10T29/49982 ,  Y10T403/47

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract translation: 本发明提供一种旋翼飞机直升机车辆杆端和制造杆端的方法。 旋转翼飞行器杆端包括具有外接合表面段和具有中心孔轴线的轴向孔的非弹性内部构件，具有内部接合表面区段和轴向孔中心孔轴线的非弹性外部构件，并且交替地模制就位 弹性垫片和非弹性垫片将非弹性内部构件连接到非弹性外部构件。 杆端包括结合到非弹性内部构件外部结合表面区段的第一内部弹性垫片和结合到非弹性外部构件内部结合表面区段和第二外部非弹性垫片的第一内部非弹性垫片和第二外部弹性垫片。 非弹性内部构件具有与外部非弹性外部构件的模制未对准旋翼机翼杆端部取向。

公开(公告)号：US07290985B2

公开(公告)日：2007-11-06

申请号：US11036737

申请日：2005-01-14

Applicant: Frank O. James ,  Christopher F. Rajecki

Inventor： Frank O. James ,  Christopher F. Rajecki

IPC: B64C11/28

CPC classification number: F16F1/40 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59 ,  F16C7/04 ,  F16C11/0614 ,  F16C11/083 ,  F16F1/393 ,  Y10T29/49885 ,  Y10T29/4998 ,  Y10T29/49982 ,  Y10T403/47

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract translation: 本发明提供一种旋翼飞机直升机车辆杆端和制造杆端的方法。 旋转翼飞行器杆端包括具有外接合表面段和具有中心孔轴线的轴向孔的非弹性内部构件，具有内部接合表面区段和轴向孔中心孔轴线的非弹性外部构件，并且交替地模制就位 弹性垫片和非弹性垫片将非弹性内部构件连接到非弹性外部构件。 杆端包括结合到非弹性内部构件外部结合表面区段的第一内部弹性垫片和结合到非弹性外部构件内部结合表面区段和第二外部非弹性垫片的第一内部非弹性垫片和第二外部弹性垫片。 非弹性内部构件具有与外部非弹性外部构件的模制未对准旋翼机翼杆端部取向。

公开(公告)号：US08632062B2

公开(公告)日：2014-01-21

申请号：US12953399

申请日：2010-11-23

Applicant: Frank O. James

Inventor： Frank O. James

IPC: F16F7/00

CPC classification number: F16F1/40 ,  B64C27/35 ,  Y10T29/4971

Abstract: An elastomeric high capacity laminated (HCL) bearing for rotary wing aircraft and method of making is provided. The elastomeric HCL bearing is mold bonded using structural adhesives with a given elastomeric subassembly tensile strength between a first metal first laminate end structural bond shim and a second metal distal laminate end structural bond shim. The structural adhesive has a limited elongation and a first end tensile strength ≧elastomeric subassembly tensile strength.

Abstract translation: 提供了一种用于旋翼飞机的弹性高容量层压（HCL）轴承及其制造方法。 弹性体HCL轴承使用在第一金属第一层压体端部结构粘结垫片和第二金属远端层压件端部结构粘合垫片之间的给定的弹性体组件拉伸强度的结构粘合剂进行模制粘合。 结构粘合剂具有有限的伸长率和第一端拉伸强度≥弹性体组件抗拉强度。

公开(公告)号：US07866025B2

公开(公告)日：2011-01-11

申请号：US11861866

申请日：2007-09-26

Applicant: Frank O. James ,  Christopher F. Rajecki

Inventor： Frank O. James ,  Christopher F. Rajecki

IPC: B23P25/00

CPC classification number: F16F1/40 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59 ,  F16C7/04 ,  F16C11/0614 ,  F16C11/083 ,  F16F1/393 ,  Y10T29/49885 ,  Y10T29/4998 ,  Y10T29/49982 ,  Y10T403/47

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract translation: 本发明提供一种旋翼飞机直升机车辆杆端和制造杆端的方法。 旋转翼飞行器杆端包括具有外接合表面段和具有中心孔轴线的轴向孔的非弹性内部构件，具有内部接合表面区段和轴向孔中心孔轴线的非弹性外部构件，并且交替地模制就位 弹性垫片和非弹性垫片将非弹性内部构件连接到非弹性外部构件。 杆端包括结合到非弹性内部构件外部结合表面区段的第一内部弹性垫片和结合到非弹性外部构件内部结合表面区段和第二外部非弹性垫片的第一内部非弹性垫片和第二外部弹性垫片。 非弹性内部构件具有与外部非弹性外部构件的模制未对准旋翼机翼杆端部取向。

公开(公告)号：US5398917A

公开(公告)日：1995-03-21

申请号：US192838

申请日：1994-02-07

Applicant: J. David Carlson ,  Michael J. Chrzan ,  Frank O. James

Inventor： J. David Carlson ,  Michael J. Chrzan ,  Frank O. James

IPC: F16F9/53 ,  F16F13/30 ,  H01F1/44 ,  F16F6/00

CPC classification number: F16F9/535 ,  F16F13/305 ,  H01F1/447

Abstract: A sealless magnetorheological fluid device is disclosed in the form of an engine mount which comprises a baffle plate (58) and a solenoid type coil (40) wrapped within a housing (20). The baffle plate diverts the flow of fluid into a more intimate contact with the coil to influence the characteristics of the fluid. The mount also comprises a first chamber (94), an elastomeric element 90 bonded to an attachment collar (88) and housing (20). An elastomeric bladder (95) is bonded to a lower surface of the housing to define a second chamber (96). Orifices (98) in housing (92) operate with coil (40) to define a valve for controlling the flow of the MR fluid.

Abstract translation: 公开了一种发动机支架形式的无密封磁流变流体装置，其包括挡板（58）和缠绕在壳体（20）内的螺线管型线圈（40）。 挡板将流体的流动转移到与线圈更紧密的接触以影响流体的特性。 安装件还包括第一室（94），弹性体元件90，其结合到附接环（88）和壳体（20）。 弹性体囊（95）结合到壳体的下表面以限定第二腔室（96）。 壳体（92）中的孔（98）与线圈（40）一起操作以限定用于控制MR流体流动的阀。

公开(公告)号：US20110206303A1

公开(公告)日：2011-08-25

申请号：US12953399

申请日：2010-11-23

Applicant: Frank O. James

Inventor： Frank O. James

IPC: F16C33/00 ,  B21D53/10

CPC classification number: F16F1/40 ,  B64C27/35 ,  Y10T29/4971

Abstract: A rotary wing aircraft bearing for providing constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes 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 elastomeric 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 having 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 laminate end structural bond shim, 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 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≧ESTS.

Abstract translation: 一种用于在第一旋转翼飞行器构件和第二旋转翼飞行器构件之间提供受限的相对运动的旋翼飞机轴承。 所述轴承包括弹性体模具粘合的层压子组件，所述弹性体模具粘合的层压子组件包括多个内部非弹性垫片构件和内部弹性垫片构件的模制粘合交替层，所述内部弹性垫片构件包括第一层压端弹性体垫片和远端 第二层压端弹性垫片。 第一层压端弹性体垫片具有接合到第一端内部非弹性垫片构件的第一侧模具和与第一金属第一层压端部结构粘合垫片接合的第二侧模具。 所述远端第二层压端部弹性体垫片具有粘合到远端第二端内部非弹性垫片构件的第一侧模具和与第二金属远端层压材料端部结构粘合垫片接合的第二侧模具，所述弹性模具粘合层压子组件具有弹性体子组件拉伸 第一金属第一层压板端部结构粘合垫片与第二金属远端层压板端部结构垫片之间的强度ESTS。 旋转翼飞行器轴承包括用于连接到第一旋转翼飞行器构件的第一端轴承连接器第一金属构件，第一端轴承连接器第一金属构件和第一金属第一端之间的第一端结构化学粘合剂环氧树脂后弹性体模 层压端部结构粘合垫片，具有至少11％的伸长率的第一端结构环氧树脂粘合剂和具有FETS≥ESSS的第一端拉伸强度FETS。

公开(公告)号：US06481894B1

公开(公告)日：2002-11-19

申请号：US09791335

申请日：2001-02-23

Applicant: Frank O. James

Inventor： Frank O. James

IPC: F16C2304

CPC classification number: F16C27/063

Abstract: A bearing that includes a first bearing support member; a second bearing support member spaced from the first bearing support member, the first and second bearing support members each having a first end and a second end; and a resilient member between the first and second bearing support members, the resilient member having a radial thickness, the radial thickness varying between the first and second ends of the bearing support members, and whereby the bearing wears substantially constantly during its useful life.

Abstract translation: 一种轴承，其包括第一轴承支撑构件; 与所述第一轴承支撑构件间隔开的第二轴承支撑构件，所述第一和第二轴承支撑构件各自具有第一端和第二端; 以及在所述第一和第二轴承支撑构件之间的弹性构件，所述弹性构件具有径向厚度，所述径向厚度在所述轴承支撑构件的第一和第二端之间变化，并且由此所述轴承在其使用寿命期间基本上不断地磨损。

公开(公告)号：US5284330A

公开(公告)日：1994-02-08

申请号：US900567

申请日：1992-06-18

Applicant: J. David Carlson ,  Michael J. Chrzan ,  Frank O. James

Inventor： J. David Carlson ,  Michael J. Chrzan ,  Frank O. James

IPC: F16F9/53 ,  F16F13/30 ,  H01F1/44 ,  F16F6/00

CPC classification number: F16F9/535 ,  F16F13/305 ,  H01F1/447

Abstract: This invention relates to sealless designs of magnetorheological fluid dampers. With these sealless designs a piston rod extends above and below a piston head within a cylindrical housing and has frustoconical elastomer elements attached to and between the rod and housing to allow translation of the piston head and rod. The piston head has a coil contained radially therein that produces magnetic flux in and around the piston. The advantages of utilizing an MR fluid according to the invention include magnetic fields which are easily produced by low voltage electromagnetic coils, damping effects which are velocity independent, and higher yield strength obtained by the MR fluid capable of generating greater damping forces.

Abstract translation: 本发明涉及磁流变流体阻尼器的无密封设计。 通过这些无缝设计，活塞杆在圆柱形壳体内上下活动头，并且具有连接到杆和壳体之间并且在杆和壳体之间的截头圆锥形弹性体元件，以允许活塞头和杆的平移。 活塞头具有径向包含的线圈，其在活塞内部和周围产生磁通。 利用根据本发明的MR流体的优点包括易于由低压电磁线圈产生的磁场，与速度无关的阻尼效应以及由能够产生更大阻尼力的MR流体获得的较高的屈服强度。