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

IPC: F16F7/00 ,  B64C27/00 ,  F16F13/24

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.

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。

公开(公告)号：US10703465B2

公开(公告)日：2020-07-07

申请号：US15942030

申请日：2018-03-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Smith ,  Maurice Griffin

IPC: B64C27/00 ,  F16F13/24

Abstract: A mounting system for a vibration isolation device comprises a support structure having an opening disposed therein, the opening having a concave recess; a thin elastomeric component attached to a surface of the concave recess; and a spherical elastomeric bearing disposed in the opening and attached to the thin elastomeric component, the spherical elastomeric bearing having a beveled upper portion, a middle portion and a beveled lower portion configured to engage the vibration isolation devices.

公开(公告)号：US20190300162A1

公开(公告)日：2019-10-03

申请号：US15942030

申请日：2018-03-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Smith ,  Maurice Griffin

IPC: B64C27/00 ,  F16F13/24

Abstract: A mounting system for a vibration isolation device comprises a support structure having an opening disposed therein, the opening having a concave recess; a thin elastomeric component attached to a surface of the concave recess; and a spherical elastomeric bearing disposed in the opening and attached to the thin elastomeric component, the spherical elastomeric bearing having a beveled upper portion, a middle portion and a beveled lower portion configured to engage the vibration isolation devices.

公开(公告)号：US20190113098A1

公开(公告)日：2019-04-18

申请号：US15785114

申请日：2017-10-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Reaugh Smith ,  Frank Bradley Stamps ,  Craig Turner ,  Maurice Griffin

IPC: F16F13/10 ,  F16F9/06 ,  F16F13/18 ,  F16F13/24

Abstract: A vibration attenuating fluid mount with a partitioned compensator includes an inner member, an outer member, a flexible member having a castellated transition between a fluid passageway and at least one operating chamber. A membrane may be disposed in a volume compensator in fluid communication with one or more operating chambers. The inner member and outer member may be connected via a castellated connection, a swaged lock ring, or a split-lock ring.

公开(公告)号：US09777788B2

公开(公告)日：2017-10-03

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 ,  B64C27/00 ,  F16F13/24

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.

公开(公告)号：US08878374B2

公开(公告)日：2014-11-04

申请号：US13766204

申请日：2013-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Craig Turner ,  Frank B. Stamps ,  Maurice Griffin

IPC: B64C11/44 ,  H02K7/18

CPC classification number: H02K7/1861 ,  H02K7/006

Abstract: A system and method to converting mechanical rotational energy of an aircraft input shaft of a transmission to electrical energy. The system includes an alternator having an inductor carried by the aircraft transmission and a magnet carried by the aircraft input shaft. The input shaft rotates the magnet in relation to the inductor, which in turn converts the mechanical rotational energy to electrical energy.

Abstract translation: 将变速器飞行器输入轴的机械旋转能量转换为电能的系统和方法。 该系统包括具有由飞行器传动器承载的电感器和由飞机输入轴承载的磁体的交流发电机。 输入轴相对于电感器旋转磁体，其又将机械旋转能转换成电能。

公开(公告)号：US20140225377A1

公开(公告)日：2014-08-14

申请号：US13766204

申请日：2013-02-13

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Craig Turner ,  Frank B. Stamps ,  Maurice Griffin

IPC: H02K7/18

CPC classification number: H02K7/1861 ,  H02K7/006

Abstract: A system and method to converting mechanical rotational energy of an aircraft input shaft of a transmission to electrical energy. The system includes an alternator having an inductor carried by the aircraft transmission and a magnet carried by the aircraft input shaft. The input shaft rotates the magnet in relation to the inductor, which in turn converts the mechanical rotational energy to electrical energy.

Abstract translation: 将变速器的飞机输入轴的机械旋转能量转换为电能的系统和方法。 该系统包括具有由飞行器传动器承载的电感器和由飞机输入轴承载的磁体的交流发电机。 输入轴相对于电感器旋转磁体，其又将机械旋转能转换成电能。