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公开(公告)号：US20190389569A1
公开(公告)日：2019-12-26
申请号：US16016280
申请日：2018-06-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Ken Shundo
Abstract: A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
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公开(公告)号：US09889927B2
公开(公告)日：2018-02-13
申请号：US14174004
申请日：2014-02-06
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Brian Modrzejewski , Ken Shundo , Frank B. Stamps , David Popelka , J. Scott Drennan , Michael E. Rinehart
IPC: B64C27/00 , F16F15/22 , B64C11/50 , G10K11/178 , B64C27/30
CPC classification number: B64C27/001 , B64C11/50 , B64C27/30 , B64C2027/004 , G10K11/178 , G10K2210/123 , G10K2210/1281
Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.
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公开(公告)号：US20170259916A1
公开(公告)日：2017-09-14
申请号：US15603019
申请日：2017-05-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Ken Shundo , Mithat Yuce , Frank B. Stamps
IPC: B64C27/80 , B64C27/52 , B64C27/51 , B64C11/48 , B64C27/35 , B64C27/32 , B64C27/10 , B64C11/02 , B64C27/48
Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.
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公开(公告)号：US10787244B2
公开(公告)日：2020-09-29
申请号：US16011721
申请日：2018-06-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Ken Shundo , Glenn Alan Shimek
Abstract: A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.
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公开(公告)号：US20190382100A1
公开(公告)日：2019-12-19
申请号：US16011721
申请日：2018-06-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Ken Shundo , Glenn Alan Shimek
Abstract: A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.
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Patent Agency Ranking
公开(公告)号：US09567070B2
公开(公告)日：2017-02-14
申请号：US13835705
申请日：2013-03-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Ken Shundo , Carlos A. Fenny , Frank B. Stamps
IPC: B64C27/10 , B64C29/00 , B64C11/32 , B64C27/605
CPC classification number: B64C29/0033 , B64C11/32 , B64C27/605
Abstract: A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.
Abstract translation: 用于转子飞行器的转子系统包括转子毂，该转子毂包括多个转子叶片，连接到转子毂的可旋转转子柱塞，包括与可旋转环接合的非旋转环的斜盘组件，多个螺距连杆， 可旋转环到多个转子叶片，以及斜盘致动器系统。 可旋转环被构造成与转子桅杆一起旋转，并且非旋转环被构造成接合和引导可旋转环。 俯仰连杆构造成控制每个转子叶片的俯仰角。 斜盘致动器系统包括：第一致动器和第二致动器，其中第一致动器和第二致动器机械地联接到固定表面和非旋转环。
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公开(公告)号：US20140271182A1
公开(公告)日：2014-09-18
申请号：US13804832
申请日：2013-03-14
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Ken Shundo , Mithat Yuce , Frank B. Stamps
CPC classification number: B64C27/80 , B64C11/02 , B64C11/48 , B64C27/10 , B64C27/322 , B64C27/35 , B64C27/48 , B64C27/51 , B64C27/52
Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.
Abstract translation: 转子组件包括与转子叶片可操作地相关联的轭。 轭包括第一装置和将转子叶片附接到轭架的第二装置。 第一装置被构造成允许转子叶片围绕弦轴线的横向运动和围绕俯仰变化轴线的旋转运动。 第二装置构造成仅允许转子叶片围绕俯仰变化轴线的旋转运动。 该方法包括围绕第一旋转平面旋转转子组件，同时在飞行期间保持相对刚性的平面外旋转和相对柔软的平面内旋转。
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公开(公告)号：US10933986B2
公开(公告)日：2021-03-02
申请号：US16016280
申请日：2018-06-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Ken Shundo
Abstract: A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
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公开(公告)号：US20200307773A1
公开(公告)日：2020-10-01
申请号：US16370368
申请日：2019-03-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Ken Shundo , Michael Dearman , Terry Thompson
Abstract: A tiltrotor controls shield having a blade or wire substructure under a fragile spinner fairing improves bird strike durability. The present disclosure discloses a spinner wind fairing with a shield structure disposed thereunder for providing protection to the proprotor assembly components. The shield structure can segment a projectile, such as a bird, that penetrates the spinner fairing into a series of smaller and lower energy elements spread across a wider area, such that the rotor components can withstand the impact of the smaller elements without damage.
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公开(公告)号：US20200023951A1
公开(公告)日：2020-01-23
申请号：US15895589
申请日：2018-02-13
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Brian Modrzejewski , Ken Shundo , Frank B. Stamps , David Popelka , J. Scott Drennan , Michael E. Rinehart
IPC: B64C27/00 , B64C11/50 , G10K11/178
Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.
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