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公开(公告)号：US10562617B2
公开(公告)日：2020-02-18
申请号：US15350073
申请日：2016-11-13
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Brad Stamps , Thomas Parham, Jr. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：US20170259911A1
公开(公告)日：2017-09-14
申请号：US15350073
申请日：2016-11-13
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Brad Stamps , Thomas Parham, JR. , Amarjit Olenchery Kizhakkepat
IPC: B64C27/00
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：US10023289B2
公开(公告)日：2018-07-17
申请号：US15044974
申请日：2016-02-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Zi Lu , Michael Seifert , Marc-Andre Rossini
IPC: B64C1/14
Abstract: According to one embodiment, a rotorcraft front windshield comprises an optically-transparent material having a non-uniform thickness profile such that the front windshield is a first thickness at a first position and a second thickness at a second position, the first thickness being different from the second thickness.
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公开(公告)号：US20160264230A1
公开(公告)日：2016-09-15
申请号：US15044974
申请日：2016-02-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Zi Lu , Michael Seifert , Marc-Andre Rossini
IPC: B64C1/14
CPC classification number: B64C1/1484
Abstract: According to one embodiment, a rotorcraft front windshield comprises an optically-transparent material having a non-uniform thickness profile such that the front windshield is a first thickness at a first position and a second thickness at a second position, the first thickness being different from the second thickness
Abstract translation: 根据一个实施例，旋翼航空器前挡风玻璃包括具有不均匀厚度轮廓的光学透明材料，使得前挡风玻璃是第一位置处的第一厚度，在第二位置处具有第二厚度，第一厚度不同于 第二厚度
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公开(公告)号：US09346561B2
公开(公告)日：2016-05-24
申请号：US14158154
申请日：2014-01-17
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew VanBuskirk , Michael Seifert
CPC classification number: B64F5/0045 , B64C27/14 , B64D45/00 , B64D2045/0085 , B64F5/60 , F16C1/04 , F16C1/08 , G01B21/24
Abstract: According to one embodiment, a system for measuring coupling misalignment of a rotorcraft drive shaft includes a reference device and a sensor. The sensor is configured to receive a signal from the reference device indicative of a distance between the reference device and the sensor. The reference device and the sensor are configured to be disposed on opposite sides of a flexible coupling coupled to the drive shaft and disposed between the engine and the pylon. The flexible coupling is configured to rotate with the drive shaft and comprises a flexure portion configured to flex in response to a difference in alignment between the engine and the pylon. A misalignment measurement system may be configured to generate a misalignment value in response to the signal.
Abstract translation: 根据一个实施例，用于测量旋翼航空器驱动轴的联轴器未对准的系统包括参考装置和传感器。 传感器被配置为从参考装置接收指示参考装置和传感器之间的距离的信号。 参考装置和传感器被配置为设置在联接到驱动轴并设置在发动机和塔架之间的柔性联轴器的相对侧上。 柔性联轴器构造成与驱动轴一起旋转并且包括被配置为响应于发动机和塔架之间的对准差而弯曲的挠曲部分。 未对准测量系统可以被配置为响应于该信号而产生未对准值。
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Patent Agency Ranking
公开(公告)号：US09260192B2
公开(公告)日：2016-02-16
申请号：US14525947
申请日：2014-10-28
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Zi Lu , Cheng-Ho Tho , Michael R. Smith , Michael Seifert
CPC classification number: B64D25/00 , B64D2201/00
Abstract: A crash attenuation system has an airbag inflatable generally adjacent to an exterior of the aircraft. The system includes a gas generator in fluid communication with an interior of the airbag. The system also includes a vent system having a vent passage supported by the aircraft, the vent passage being configured to allow gas to escape from within the airbag during an impact to a second set of airbags for flotation. The vent system also includes an actuator door for sealing the vent passage, thereby preventing gas from leaving the airbag. The actuator door is actuated by an actuator, the actuator being in fluid communication with the gas generator through an actuator duct. The system operates such that deployment of gas from the gas generator causes the actuator to inflate, thereby causing the actuator door to seal the vent passage. The gas generator is configured to re-inflate the airbag after the actuator door seals the vent passage.
Abstract translation: 碰撞衰减系统具有通常与飞机外部相邻的气囊充气。 该系统包括与气囊的内部流体连通的气体发生器。 该系统还包括具有由飞行器支撑的通气通道的通气系统，该排气通道构造成允许气体在冲击期间从气囊内逸出到用于浮选的第二组安全气囊。 排气系统还包括用于密封通气通道的致动器门，从而防止气体离开气囊。 致动器门由致动器致动，致动器通过致动器导管与气体发生器流体连通。 系统操作使得来自气体发生器的气体展开使致动器膨胀，从而使致动器门密封通气通道。 气体发生器构造成在致动器门密封通气通道之后再次充气气囊。
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公开(公告)号：US11084575B2
公开(公告)日：2021-08-10
申请号：US16084970
申请日：2017-03-14
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Bradley Stamps , Thomas Parham, Jr. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：US09452843B1
公开(公告)日：2016-09-27
申请号：US14711230
申请日：2015-05-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Zi Lu , Michael Seifert , Cheng-Ho Tho
CPC classification number: B64D25/00 , B64C25/32 , B64C25/56 , B64C2025/325 , B64D2201/00
Abstract: An aircraft airbag inflation system includes an airbag mounted on an external surface of an aircraft. The airbag is configured to inflate in one of multiple stages prior to the aircraft crashing, and each stage is associated with a respective pressure. The system also includes multiple sensors disposed on-board the aircraft and configured to sense aircraft velocities and an aircraft attitude. The system also includes a controller disposed on-board the aircraft and configured to receive multiple signals from the sensors, the multiple signals representing the aircraft velocities and the aircraft attitude sensed by the sensors, determine a crash event for the aircraft based on the received multiple signals, the crash event including an aircraft sink rate, an aircraft attitude at crash time, and an aircraft distance from the impact surface, and determine a stage at which the airbag is to be inflated based on the crash event.
Abstract translation: 飞机安全气囊充气系统包括安装在飞行器的外表面上的安全气囊。 气囊被构造成在飞机撞击之前的多个阶段中的一个中膨胀，并且每个阶段与相应的压力相关联。 该系统还包括布置在飞行器上的多个传感器并且被配置成感测飞行器速度和飞行器姿态。 该系统还包括设置在飞行器上的控制器，并被配置为从传感器接收多个信号，表示飞行器速度的多个信号和由传感器感测到的飞行器姿态基于接收到的多个飞行器确定飞机的碰撞事件 信号，碰撞事件包括飞机下沉速率，飞机在碰撞时的姿态，以及与撞击表面的飞行器距离，以及基于碰撞事件确定气囊膨胀的阶段。
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公开(公告)号：US20140207332A1
公开(公告)日：2014-07-24
申请号：US14158154
申请日：2014-01-17
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Matthew VanBuskirk , Michael Seifert
IPC: B64F5/00
CPC classification number: B64F5/0045 , B64C27/14 , B64D45/00 , B64D2045/0085 , B64F5/60 , F16C1/04 , F16C1/08 , G01B21/24
Abstract: According to one embodiment, a system for measuring coupling misalignment of a rotorcraft drive shaft includes a reference device and a sensor. The sensor is configured to receive a signal from the reference device indicative of a distance between the reference device and the sensor. The reference device and the sensor are configured to be disposed on opposite sides of a flexible coupling coupled to the drive shaft and disposed between the engine and the pylon. The flexible coupling is configured to rotate with the drive shaft and comprises a flexure portion configured to flex in response to a difference in alignment between the engine and the pylon. A misalignment measurement system may be configured to generate a misalignment value in response to the signal.
Abstract translation: 根据一个实施例，用于测量旋翼航空器驱动轴的联轴器未对准的系统包括参考装置和传感器。 传感器被配置为从参考装置接收指示参考装置和传感器之间的距离的信号。 参考装置和传感器被配置为设置在联接到驱动轴并设置在发动机和塔架之间的柔性联轴器的相对侧上。 柔性联轴器构造成与驱动轴一起旋转并且包括被配置为响应于发动机和塔架之间的对准差而弯曲的挠曲部分。 未对准测量系统可以被配置为响应于该信号而产生未对准值。
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公开(公告)号：US10232936B2
公开(公告)日：2019-03-19
申请号：US15359305
申请日：2016-11-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Seifert , Peter Quinn Romano , Thomas Parham
Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.
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