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公开(公告)号：US10400818B2
公开(公告)日：2019-09-03
申请号：US14959589
申请日：2015-12-04
IPC分类号： F16C19/48 , B64C9/02 , B64C9/22 , B64D45/02 , F16C33/74 , F16C11/02 , F16C17/10 , F16C23/04 , F16C29/04 , F16C33/60 , F16C33/78
摘要： A track roller assembly includes a split inner ring, a split outer ring, a one piece inner ring and/or a one piece outer ring and a liner or plurality of rolling elements engaging therewith, the track roller assembly being disposed in a structure of an Airbus A-350 aircraft, an Airbus A-320 aircraft, an Airbus A320Neo aircraft, an Airbus A330 aircraft, an Airbus A330Neo aircraft, an Airbus A321 aircraft, an Airbus A340 aircraft, and an Airbus A380 aircraft.
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公开(公告)号：US20190264746A1
公开(公告)日：2019-08-29
申请号：US16282727
申请日：2019-02-22
摘要： A composite material having an alloy matrix including titanium, aluminum, niobium, manganese, boron, and carbon is disclosed. The composite material includes, by atomic percentage, 40.0% to 50.0% Al, 1.0% to 8.0% Nb, 0.5% to 2.0% Mn, 0.1% to 2.0% B, and 0.01% to 0.2% C. The composite material is doped with a solid lubricant such as MoS2, ZnO, CuO, hexagonal boron nitride (hBN), WS2, AgTaO3, CuTaO3, CuTa2O6, or combinations thereof. Components composed of the composite material exhibit increased ductility at room temperature and reduced fracture tendency, resulting in improved durability.
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公开(公告)号：US09926972B2
公开(公告)日：2018-03-27
申请号：US15295185
申请日：2016-10-17
发明人： Jarrod McGuire , Matthew Porter
CPC分类号： F16C11/0652 , E04B1/985 , E04H9/023 , F16C11/0604 , F16C11/0628 , F16C11/0633 , F16C11/068 , F16C2202/50 , F16C2208/02 , F16C2208/20 , F16C2208/82 , F16C2361/53 , F16F7/104 , Y10T403/32737
摘要： A spheroidal joint for a tuned mass damper system includes a base having a concave seat and a lubricious liner secured thereto. The base defines a first mounting portion under the concave seat and a circumferential rim opposite the first mounting portion. The concave seat tapers radially outward to define a chamfer which terminates at a radially inner edge of the rim. The spheroidal joint includes an inner member that has a convex seat. The inner member has a second mounting portion extending from the convex seat and an indentation circumferentially extending around the inner member between the convex seat and the second mounting portion. The indentation cooperates with the chamfer for misalignment of the inner member relative to the base. The convex seat slidingly engages the lubricious liner.
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公开(公告)号：US09890814B2
公开(公告)日：2018-02-13
申请号：US14728426
申请日：2015-06-02
发明人： Alex Habibvand
CPC分类号： F16C33/4676 , B64C9/00 , B64C9/16 , F16C11/0614 , F16C19/38 , F16C19/381 , F16C23/086 , F16C33/4682 , F16C33/48 , F16C33/497 , F16C2240/44 , F16C2326/43
摘要： A cage for an hourglass roller bearing includes an annular ring having a first axial face and a second axial face. A plurality of first rails extend from the first axial face and a plurality of second rails extend from the second axial face. The cage includes a plurality of pockets. Each of the plurality of pockets is defined by opposing circumferentially facing walls of at least one of adjacent pairs of the first rails and adjacent pairs of the second rails. The circumferentially facing walls are arcuately formed so that each of the plurality of pockets is cylindrical.
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公开(公告)号：US20180003234A1
公开(公告)日：2018-01-04
申请号：US15634186
申请日：2017-06-27
发明人： James Voisine
CPC分类号： F16C33/74 , F16C23/043 , F16C23/045 , F16C33/743 , F16J15/3232
摘要： A flexible double lipped annular seal includes an anchor segment at a radially outermost portion thereof and having a pocket formed therein. The annular seal includes a branch segment extending axially outward and radially inward from the first leg at an angle. A first lip seal and a second lip seal extend radially inward from the branch segment and have a gap therebetween. The branch segment terminates in a stub segment. The annular seal includes a metallic shield secured to the annular seal and a portion of which seats in the pocket.
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公开(公告)号：US09856910B2
公开(公告)日：2018-01-02
申请号：US15359828
申请日：2016-11-23
发明人： Andy Tyler , Ryan Peaslee , Michael Heligman , David Coombe , Matthias Duenner , Philippe Charmillot
CPC分类号： F16C25/04 , B64C3/56 , F16C17/04 , F16C17/10 , F16C27/063 , F16C33/04 , F16C33/201 , F16C2202/52 , F16C2208/10 , F16C2208/32 , F16C2208/70 , F16C2229/00 , F16C2326/43
摘要： A bearing for a hinge in a hinged raked aircraft wing tip includes an outer member that has a concave inner surface and an inner member that has first and second inner segments. Each of the first and second inner segments has a base that has a bearing section extending therefrom. The bearing sections together form a convex outer surface that is complementary in shape to the concave inner surface. A preload feature is positioned between and engages a portion of the bearing sections. A lubricous liner is positioned between the concave inner surface and the convex outer surface. The bearing sections are positioned in the outer member to compress the preload feature to limit axial movement between the outer and inner members to a predetermined magnitude. The preload feature flexes outward as a result of wear to the liner to maintain the axial movement to the predetermined magnitude.
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公开(公告)号：US09841048B2
公开(公告)日：2017-12-12
申请号：US15060702
申请日：2016-03-04
发明人： Eric Lambert , Scott McNeil
CPC分类号： B64C1/1407 , B64C25/16 , F16C17/10 , F16C17/246 , F16C17/26 , F16C33/1095 , F16C2208/32 , F16C2326/43 , F16F9/3214 , F16F9/3278
摘要： A rotation rod assembly includes a first linkage rod having a first bore extending therein. The rotation rod assembly includes a second linkage rod having a piston section extending axially therefrom, the piston section is disposed for rotation in the first bore. The piston section is axially restrained in the bore. The piston section has a self-lubricating liner secured to at least one outer surface thereof. The self-lubricating liner is in sliding engagement with portions of the bore. The liner is secured to the radially and/or axially outer surfaces of the piston section and has at least one groove therein for collection of wear materials and debris.
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公开(公告)号：US20170108034A1
公开(公告)日：2017-04-20
申请号：US15295185
申请日：2016-10-17
发明人： Jarrod McGuire , Matthew Porter
IPC分类号： F16C11/06
CPC分类号： F16C11/0652 , E04B1/985 , E04H9/023 , F16C11/0604 , F16C11/0628 , F16C11/0633 , F16C11/068 , F16C2202/50 , F16C2208/02 , F16C2208/20 , F16C2208/82 , F16C2361/53 , F16F7/104 , Y10T403/32737
摘要： A spheroidal joint for a tuned mass damper system includes a base having a concave seat and a lubricious liner secured thereto. The base defines a first mounting portion under the concave seat and a circumferential rim opposite the first mounting portion. The concave seat tapers radially outward to define a chamfer which terminates at a radially inner edge of the rim. The spheroidal joint includes an inner member that has a convex seat. The inner member has a second mounting portion extending from the convex seat and an indentation circumferentially extending around the inner member between the convex seat and the second mounting portion. The indentation cooperates with the chamfer for misalignment of the inner member relative to the base. The convex seat slidingly engages the lubricious liner.
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公开(公告)号：US20160327091A1
公开(公告)日：2016-11-10
申请号：US14572260
申请日：2014-12-16
CPC分类号： F16C33/36 , B64C9/16 , B64C9/18 , B64C13/28 , F16C11/06 , F16C19/38 , F16C23/086 , F16C23/088 , F16C2240/70 , F16C2326/43
摘要： An edge flap arrangement for an aircraft wing includes a main flap element and an actuator for moving the main flap element relative to the aircraft wing. A linkage arrangement supports the main flap element and includes a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and the drop link are connected by a hinge point having an hourglass bearing assembly having hourglass shaped rollers with a circular cross section symmetrical about a longitudinal axis, first and second axial ends, and an exterior surface. The exterior surface defines a concave engagement surface having a first radius of curvature R1 and a second radius of curvature which is greater than the first radius of curvature R1. The first radius of curvature is between 50 and 95 percent of the second radius of curvature.
摘要翻译： 用于飞机机翼的边缘翼片装置包括主翼片元件和用于相对于飞机机翼移动主翼片元件的致动器。 连接装置支撑主翼片元件并且包括具有固定到飞机机翼的固定支柱的下降铰链连接装置和固定到主翼片元件的下降连杆。 固定支柱和下降连杆通过铰链点连接，铰链点具有沙漏轴承组件，该沙漏轴承组件具有沙漏形滚子，其具有围绕纵向轴线，第一和第二轴向端部以及外部表面对称的圆形横截面。 外表面限定具有第一曲率半径R1和大于第一曲率半径R1的第二曲率半径的凹形接合表面。 第一曲率半径在第二曲率半径的50％至95％之间。
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20.发明授权System for isolating electrical current in a bearing for use in an aircraft structure 有权用于隔离用于飞机结构的轴承中的电流的系统公开(公告)号：US09482269B2
公开(公告)日：2016-11-01
申请号：US14857055
申请日：2015-09-17
发明人： John W. Fruin , Ben Anderson , Maura Simpson , Andrew Henn , Kevin Bryant
CPC分类号： F16C17/24 , B64D45/02 , F16C23/043 , F16C23/045 , F16C33/201 , F16C33/74 , F16C2326/43
摘要： A system for isolating electrical current in an aircraft structure includes a first structure a bearing having an outer race and an inner race and a liner disposed therebetween, the outer race having a second structure coupled thereto. A dielectric seal is secured to the outer race and engages the inner race. A conditionally non-conductive gas occupies a sealed chamber that defines a gap between the inner race and the outer race. The gap has a predetermined magnitude sufficient to prevent electrical arcing or current leakage between the inner race and the outer race at a first voltage less than that voltage resulting from a lightning strike; and/or to conduct an electrical current between the inner race and the outer race at a second voltage greater than or equal to the voltage resulting from the lightning strike.
摘要翻译： 用于隔离飞行器结构中的电流的系统包括第一结构，具有外座圈和内座圈以及设置在其间的衬套的轴承，所述外座圈具有与其连接的第二结构。 绝缘密封件固定到外座圈并与内座圈接合。 有条件的非导电气体占据限定内圈和外圈之间的间隙的密封腔。 间隙具有足以防止内圈和外座圈之间的电弧或电流泄漏小于由雷击引起的电压的第一电压的预定大小; 和/或以大于或等于雷击所产生的电压的第二电压在内座圈和外座圈之间传导电流。
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