-
公开(公告)号：US20140271214A1
公开(公告)日：2014-09-18
申请号：US13829191
申请日：2013-03-14
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Drew Sutton , Jeffrey P. Nissen , Andrew Haldeman
CPC classification number: F01D5/282 , B23P15/04 , B64C11/205 , B64C27/473 , C22C45/00 , Y10T29/49337
Abstract: A rotor blade abrasion strip and method to manufacturing the same. The abrasion strip being composed of a molded amorphous metal contoured to match a leading edge outer surface of the rotor blade. The abrasion strip being configured to removably attach to a leading edge of the rotor blade and configured to prevent damage to the leading edge during flight. The method includes molding the abrasion strip with the amorphous metal.
Abstract translation: 转子叶片磨损条及其制造方法。 磨损条由成型的非晶金属组成，其形状匹配转子叶片的前缘外表面。 所述磨耗条构造成可拆卸地附接到所述转子叶片的前缘并且构造成防止在飞行期间损坏所述前缘。 该方法包括用无定形金属模制耐磨条。
-
公开(公告)号：US10654567B2
公开(公告)日：2020-05-19
申请号：US14669977
申请日：2015-03-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Sutton
IPC: B64C27/46 , B64C27/48 , B64C27/473
Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.
-
Patent Agency Ranking
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.
-
公开(公告)号：US10086934B2
公开(公告)日：2018-10-02
申请号：US15362424
申请日：2016-11-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Maresh , Frank Bradley Stamps , Patrick Ryan Tisdale , Robert Patrick Wardlaw , Andrew Haldeman , Drew Alan Sutton
Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.
-
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.
-
16.发明申请公开(公告)号：US20170073067A1
公开(公告)日：2017-03-16
申请号：US15362424
申请日：2016-11-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Maresh , Frank Bradley Stamps , Patrick Ryan Tisdale , Robert Patrick Wardlaw , Andrew Haldeman , Drew Alan Sutton
Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.
Abstract translation: 毂系统包括至少一个轭，至少一个剪切轴承和至少一个桅杆适配器。 所述至少一个桅杆适配器构造成支撑所述至少一个轭和所述至少一个剪切轴承，并且所述至少一个轭具有与所述至少一个剪切轴承的扑动铰链不重合的扑动铰链。 另一个集线器系统包括堆叠的轭和桅杆适配器。 桅杆适配器被配置为将旋转从转子桅杆传递到轮毂系统，以围绕中心旋转轴线旋转轮毂系统。 桅杆适配器还被配置为支撑堆叠的轭架，使得堆叠的轭架中的每个轭架构造成适应围绕垂直于或大致垂直于中心旋转轴线的轴线的至少一定量的旋转。
-
公开(公告)号：US20160280367A1
公开(公告)日：2016-09-29
申请号：US14669977
申请日：2015-03-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Haldeman , Frank Bradley Stamps , Drew Sutton
IPC: B64C27/46
CPC classification number: B64C27/46 , B64C27/48 , B64C2027/4736
Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.
Abstract translation: 转子叶片组件包括转子叶片，其包括内侧端部和外侧端部。 由复合材料制成的复合轭配件安装在转子叶片上。 复合轭配件包括插入转子叶片的内侧端部的外侧部分，内侧部分和弯曲区域，转子叶片围绕弯曲区域弯曲。 内侧部分和挠曲区域在转子叶片的外侧。
-
-
-
-
-
-
Search Results
17
records
(took 0.025 seconds)
