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公开(公告)号：US10384771B2
公开(公告)日：2019-08-20
申请号：US15600229
申请日：2017-05-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Alan Sutton , James Donn Hethcock
IPC: B64C27/35 , B64C27/32 , B64C29/00 , B64C27/48 , B64C27/41 , B64C27/52 , B64C27/82 , F01D7/00 , B64C27/78
Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.
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公开(公告)号：US20190061926A1
公开(公告)日：2019-02-28
申请号：US15683621
申请日：2017-08-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Frank B. Stamps , James Donn Hethcock
Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.
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公开(公告)号：US09657582B2
公开(公告)日：2017-05-23
申请号：US13800174
申请日：2013-03-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Sutton , James Donn Hethcock
CPC classification number: B64C27/35 , B64C27/32 , B64C27/41 , B64C27/48 , B64C27/52 , B64C27/78 , B64C27/82 , B64C29/0033 , F01D7/00
Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.
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公开(公告)号：US20190061930A1
公开(公告)日：2019-02-28
申请号：US15687350
申请日：2017-08-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Dalton T. Hampton , Timothy Kent Ledbetter , Drew A. Sutton , Bryan W. Marshall , Paul Sherrill , Frank B. Stamps , James Donn Hethcock , Andrew Paul Haldeman , Paul K. Oldroyd
IPC: B64C27/473 , B64C27/06 , B64F5/40 , B29C73/04
Abstract: In one embodiment, a method may comprise coupling a plurality of reinforcement fibers to a plurality of spherical components; inserting the plurality of spherical components into an enclosure; and heating the enclosure to cause the plurality of spherical components to expand, wherein the plurality of spherical components expands to form a geodesic structure, wherein the geodesic structure comprises a plurality of polyhedron components configured in a geodesic arrangement.
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公开(公告)号：US20160089830A1
公开(公告)日：2016-03-31
申请号：US14496275
申请日：2014-09-25
Applicant: Bell Helicopter Textron Inc.
Inventor： James Donn Hethcock , Dave Carlson , Paul K. Oldroyd
IPC: B29C65/00
CPC classification number: B32B37/1284 , B29C44/08 , B29C44/1223 , B29L2031/082 , B29L2031/3076 , B29L2031/3088 , B29L2031/608 , B32B3/12 , B32B5/20 , B32B27/08 , B32B27/40 , B32B37/182 , B32B2266/0278 , B32B2605/18
Abstract: One aspect of a process of forming an aircraft component includes bonding a first end of a honeycomb structure to a surface of an aircraft skin member, the honeycomb structure including multiple connected cells. Foam is sprayed on a second end of the honeycomb structure opposite the first end. The process also includes curing the foam on the second end of the honeycomb structure.
Abstract translation: 形成飞行器部件的方法的一个方面包括将蜂窝结构的第一端接合到飞机蒙皮构件的表面，所述蜂窝结构包括多个连接的单元。 将泡沫喷涂在与第一端相对的蜂窝结构体的第二端。 该方法还包括在蜂窝结构的第二端固化泡沫。
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Patent Agency Ranking
6.发明申请Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation 有权具有球形弹性离心力的平衡尾部转子毂用于刀片保持和间距变化铰接公开(公告)号：US20140271180A1
公开(公告)日：2014-09-18
申请号：US13800174
申请日：2013-03-13
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Sutton , James Donn Hethcock
IPC: F01D7/00
CPC classification number: B64C27/35 , B64C27/32 , B64C27/41 , B64C27/48 , B64C27/52 , B64C27/78 , B64C27/82 , B64C29/0033 , F01D7/00
Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.
Abstract translation: 转子毂包括万向节组件和弹性离心力轴承。 万向节组件构造成将桅杆的旋转运动传递到转子轮毂，并且使得转子轮毂能够相对于桅杆折叠。 弹性体离心力轴承构造成当桅杆旋转时承受转子叶片的离心力，并且构造成适应转子叶片的桨距变化。 一种方法包括设计一个万向架组件，其使得尾部转子毂能相对于尾部转子桅杆折叠。 选择离心力轴承，使离合力叶片能够承受离心力，并允许尾部转子叶片间距改变铰接。 然后，提供说明书以在平面内转子组件中使用万向架组件和离心力轴承。
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公开(公告)号：US10668705B2
公开(公告)日：2020-06-02
申请号：US15625538
申请日：2017-06-16
Applicant: Bell Helicopter Textron Inc.
Inventor： James Donn Hethcock , Dave Carlson , Paul K. Oldroyd
IPC: B32B37/12 , B29C44/12 , B29C44/08 , B32B3/12 , B32B5/20 , B32B27/08 , B32B27/40 , B32B37/18 , B29L31/30 , B29L31/08 , B29L31/60
Abstract: One aspect of a process of forming an aircraft component includes bonding a first end of a honeycomb structure to a surface of an aircraft skin member, the honeycomb structure including multiple connected cells. Foam is sprayed on a second end of the honeycomb structure opposite the first end. The process also includes curing the foam on the second end of the honeycomb structure.
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公开(公告)号：US10597143B2
公开(公告)日：2020-03-24
申请号：US15683621
申请日：2017-08-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Frank B. Stamps , James Donn Hethcock
IPC: B64C11/02 , B64C27/35 , B64C11/04 , B64C11/06 , B64C27/39 , B64C27/12 , B64C27/32 , B64C27/59 , B64C27/78
Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.
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9.发明申请公开(公告)号：US20170259913A1
公开(公告)日：2017-09-14
申请号：US15600229
申请日：2017-05-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Alan Sutton , James Donn Hethcock
CPC classification number: B64C27/35 , B64C27/32 , B64C27/41 , B64C27/48 , B64C27/52 , B64C27/78 , B64C27/82 , B64C29/0033 , F01D7/00
Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.
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公开(公告)号：US20170291406A1
公开(公告)日：2017-10-12
申请号：US15625538
申请日：2017-06-16
Applicant: Bell Helicopter Textron Inc.
Inventor： James Donn Hethcock , Dave Carlson , Paul K. Oldroyd
CPC classification number: B32B37/1284 , B29C44/08 , B29C44/1223 , B29L2031/082 , B29L2031/3076 , B29L2031/3088 , B29L2031/608 , B32B3/12 , B32B5/20 , B32B27/08 , B32B27/40 , B32B37/182 , B32B2266/0278 , B32B2605/18
Abstract: One aspect of a process of forming an aircraft component includes bonding a first end of a honeycomb structure to a surface of an aircraft skin member, the honeycomb structure including multiple connected cells. Foam is sprayed on a second end of the honeycomb structure opposite the first end. The process also includes curing the foam on the second end of the honeycomb structure.
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