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公开(公告)号：US11173521B2
公开(公告)日：2021-11-16
申请号：US16284931
申请日：2019-02-25
Applicant: Bell Helicopter Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Gary Miller , Richard E. Rauber , Thomas C. Parham, Jr. , Michael R. Smith , Michael Scott Seifert , Jouyoung Jason Choi
Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.
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公开(公告)号：US10933984B2
公开(公告)日：2021-03-02
申请号：US16035358
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , Eric Gonzalez , Michael R. Smith
Abstract: Systems and methods include providing a coaxial helicopter with a main rotor system having an upper rotor system, a coaxial counter-rotating lower rotor system, and a rotor mast assembly having an upper rotor mast and a coaxial counter-rotating lower rotor mast. The upper rotor system and an associated upper vibration reduction system are coupled to the upper rotor mast. The upper vibration reduction system provides in-plane vibration control and reduction to the upper rotor system. The lower rotor system and an associated lower vibration reduction system are coupled to the lower rotor mast. The lower vibration reduction system provides in-plane vibration control and reduction to the lower rotor system. A third vibration reduction system is coupled to the rotor mast assembly and cooperates with the upper and lower vibration reduction systems to provide total in-plane vibration control and reduction to the main rotor system.
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公开(公告)号：US20200017203A1
公开(公告)日：2020-01-16
申请号：US16035358
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , Eric Gonzalez , Michael R. Smith
Abstract: Systems and methods include providing a coaxial helicopter with a main rotor system having an upper rotor system, a coaxial counter-rotating lower rotor system, and a rotor mast assembly having an upper rotor mast and a coaxial counter-rotating lower rotor mast. The upper rotor system and an associated upper vibration reduction system are coupled to the upper rotor mast. The upper vibration reduction system provides in-plane vibration control and reduction to the upper rotor system. The lower rotor system and an associated lower vibration reduction system are coupled to the lower rotor mast. The lower vibration reduction system provides in-plane vibration control and reduction to the lower rotor system. A third vibration reduction system is coupled to the rotor mast assembly and cooperates with the upper and lower vibration reduction systems to provide total in-plane vibration control and reduction to the main rotor system.
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公开(公告)号：US20190202570A1
公开(公告)日：2019-07-04
申请号：US16297179
申请日：2019-03-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael R. Smith , Cheng-Ho Tho
CPC classification number: B64D25/00 , B64C25/56 , B64D45/00 , B64D2045/008
Abstract: An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.
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公开(公告)号：US20180038439A1
公开(公告)日：2018-02-08
申请号：US15723510
申请日：2017-10-03
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Taeoh Lee , David E. Heverly, II , Matthew W. Hendricks , Maurice Griffin , Michael R. Smith
CPC classification number: F16F7/00 , B64C27/001 , B64C2027/002 , F16F13/24
Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
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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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7.发明申请ROTORCRAFT VIBRATION SUPPRESSION SYSTEM IN A FOUR CORNER PYLON MOUNT CONFIGURATION 有权四角墩安装配置中的ROTORCRAFT振动抑制系统公开(公告)号：US20130270415A1
公开(公告)日：2013-10-17
申请号：US13736687
申请日：2013-01-08
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Taeoh Lee , David E. Heverly, II , Matthew W. Hendricks , Maurice Griffin , Michael R. Smith
IPC: F16F7/00
CPC classification number: F16F7/00 , B64C27/001 , B64C2027/002 , F16F13/24
Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
Abstract translation: 振动抑制系统包括位于四角塔架安装结构组件的每个角落中的隔振器。 四个隔振器的组合，两个位于变速器前方，两个位于变速器的后面，共同有效地隔离主转子垂直剪切，俯仰力矩以及滚动力矩引起的振动。 每个相对的隔振器对可以有效地反应瞬间振动，因为瞬间可以在每个隔振器处分解成两个对立的垂直振荡。 吊架结构在一对隔振器之间延伸，从而允许隔振器与振动体隔开，以提供增加的控制。
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公开(公告)号：US20200156773A1
公开(公告)日：2020-05-21
申请号：US16197761
申请日：2018-11-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , David Heverly , Michael R. Smith , Michael Scott Seifert , Thomas C. Parham, JR. , Gary Miller , Jouyoung Jason Choi , Richard E. Rauber
IPC: B64C27/00
Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.
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公开(公告)号：US09254914B2
公开(公告)日：2016-02-09
申请号：US14086446
申请日：2013-11-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew W. Hendricks , Maurice D. Griffin , Michael R. Smith , Taeoh Lee
CPC classification number: B64C27/001 , B64C2027/002 , B64C2027/004 , F16F15/10
Abstract: A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation.
Abstract translation: 用于飞行器中的变速器的约束系统可以包括具有第一流体室的第一支柱，与第一弹性体构件弹性地联接到第一壳体的第一活塞。 约束系统可以包括具有第二流体室的第二支柱，与第二弹性构件弹性地联接到第二壳体的第二活塞。 约束系统可以包括在第一流体室和第二流体室之间的流体管线。 第一支柱和第二支柱不仅集中提供扭矩约束，而且还提供扭矩测量和前/后隔振。
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公开(公告)号：US09249856B1
公开(公告)日：2016-02-02
申请号：US14218521
申请日：2014-03-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Taeoh Lee , Maurice D. Griffin , Michael R. Smith , Michael Seifert
IPC: F16F13/08
CPC classification number: F16F13/24 , B64C27/001 , B64C2027/004 , F16F2224/04
Abstract: A vibration isolator can include an upper housing defining an upper fluid chamber; a lower housing defining a lower fluid chamber; a piston resiliently coupled to the upper housing with an upper elastomer member, the piston being resiliently coupled to the lower housing with a lower elastomer member; a tuning passage associated with the piston; and a tuning fluid disposed within the upper fluid chamber, the lower fluid chamber, and the tuning passage, the tuning fluid comprising a polytungstate.
Abstract translation: 隔振器可以包括限定上流体室的上壳体; 限定下部流体室的下部壳体; 活塞通过上弹性体弹性地联接到上壳体，活塞用下弹性体弹性地联接到下壳体; 调节通道与活塞相关联; 以及设置在上流体室内的调谐流体，下流体室和调谐通道，调谐流体包括多钨酸盐。
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