公开(公告)号：US11738859B2

公开(公告)日：2023-08-29

申请号：US17627462

申请日：2020-06-25

申请人： LEONARDO S.P.A.

发明人： Luigi Bottasso ,  Ermanno Fosco ,  Paolo Pisani ,  Francesco Vincenzo ,  Francesco Rosa ,  Francesco Braghin ,  Gabriele Cazzulani ,  Simone Cinquemani

IPC分类号： B64C27/00

CPC分类号： B64C27/001 ,  B64C2027/003 ,  B64C2027/004 ,  B64C2027/005

摘要： A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.

公开(公告)号：US20180257765A1

公开(公告)日：2018-09-13

申请号：US15457605

申请日：2017-03-13

申请人： The Boeing Company

发明人： Robert C. Derham ,  Gregory R. Turk

IPC分类号： B64C27/00 ,  G05D1/00 ,  B64D43/02 ,  G01P13/02

CPC分类号： B64C27/001 ,  B64C2027/004 ,  B64D43/02 ,  B64D45/00 ,  G01P13/025 ,  G05D1/0066

摘要： Systems and methods for cueing a helicopter pilot when a flight parameter (such as rotor-induced vibration level, airspeed, bank angle, icing accumulation, etc.) exceeds operational constraints. This is accomplished by reformulating the on-board cockpit active vibration control system to add a pilot cueing aid. When the measured flight parameter becomes excessive, the active vibration control system is temporarily detuned, which reduces the amount of vibration suppression it provides or turns off vibration suppression, causing an increase in airframe vibration levels to cue the pilot to take action (e.g., to fly within operating limits).

公开(公告)号：US20180231986A1

公开(公告)日：2018-08-16

申请号：US15515949

申请日：2015-09-29

申请人： Sikorsky Aircraft Corporation

发明人： Matthew A. White ,  Matthew T. Luszcz

IPC分类号： G05D1/08 ,  G05D1/00 ,  B64C27/82 ,  B64C27/10

CPC分类号： F16F15/02 ,  B64C13/04 ,  B64C13/50 ,  B64C27/001 ,  B64C27/006 ,  B64C27/10 ,  B64C27/14 ,  B64C27/467 ,  B64C27/57 ,  B64C2027/004 ,  B64C2027/8236 ,  B64D35/06 ,  G05D1/0816 ,  G05D1/0858

摘要： An aircraft includes an airframe with an upper portion and an extending tail, a counter-rotating, coaxial main rotor assembly disposed at the upper portion of the airframe, a translational thrust system, including a propeller, disposed at the extending tail of the airframe and a flight control system configured to control at least one of revolutions-per-minute (RPM) and pitch of the propeller of the translational thrust system in response to an input speed or acceleration command.

公开(公告)号：US20170341739A1

公开(公告)日：2017-11-30

申请号：US15536478

申请日：2015-10-15

申请人： Sikorsky Aircraft Corporation

发明人： Jordan Alex Kaye ,  Marcus D. Cappelli ,  Michael Monico

IPC分类号： B64C27/00 ,  B64C27/14 ,  B64C27/32 ,  B64C27/82

CPC分类号： B64C27/001 ,  B06B1/164 ,  B64C27/14 ,  B64C27/32 ,  B64C27/82 ,  B64C2027/004 ,  B64C2027/005 ,  F16F7/1005

摘要： A force generator includes a hub, which is rotatable about an axis thereof, an elongate member coupled to the hub such that the elongate member is rotatable with the hub and extends radially outwardly away from the hub and the axis along a radial dimension defined with respect to the axis and a mass, which is movably disposed along the elongate member and is adjustable to multiple radial mass positions relative to the hub.

公开(公告)号：US20170297685A1

公开(公告)日：2017-10-19

申请号：US15277756

申请日：2016-09-27

申请人： Textron Innovations Inc.

发明人： David Heverly ,  David A. Popelka ,  Frank B. Stamps

IPC分类号： B64C27/00 ,  B64C11/00 ,  B64C29/00

CPC分类号： B64C27/001 ,  B64C11/008 ,  B64C29/0033 ,  B64C2027/003 ,  B64C2027/004 ,  B64C2027/005

摘要： A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.

公开(公告)号：US20170283049A1

公开(公告)日：2017-10-05

申请号：US15508321

申请日：2015-08-07

申请人： Sikorsky Aircraft Corporation

发明人： Steven D. Weiner

IPC分类号： B64C27/33 ,  B64C27/82 ,  B64C27/10 ,  B64C27/48 ,  B64C27/32

CPC分类号： F16F15/02 ,  B64C13/04 ,  B64C13/50 ,  B64C27/001 ,  B64C27/006 ,  B64C27/10 ,  B64C27/14 ,  B64C27/467 ,  B64C27/57 ,  B64C2027/004 ,  B64C2027/8236 ,  B64D35/06 ,  G05D1/0816 ,  G05D1/0858

摘要： A differential pre-cone rotary wing arrangement includes a first rotor assembly having a first set of rotor blades rotatable about an axis, the first set of rotor blades having a first pre-cone angle, and a second rotor assembly having a second set of rotor blades rotatable about the axis, the second set of rotor blades having a second pre-cone angle, the second pre-cone angle is different than the first pre-cone angle.

公开(公告)号：US09452828B2

公开(公告)日：2016-09-27

申请号：US14231940

申请日：2014-04-01

申请人： Textron Innovations Inc.

发明人： David Heverly ,  David A. Popelka ,  Frank B. Stamps

IPC分类号： B64C27/00 ,  B64C11/00 ,  B64C29/00

CPC分类号： B64C27/001 ,  B64C11/008 ,  B64C29/0033 ,  B64C2027/003 ,  B64C2027/004

摘要： A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.

摘要翻译： 用于飞行器的振动衰减器具有安装在飞行器的转子轮毂的旋转系统中的至少一个重量，每个重量可围绕毂相对于轮毂的旋转轴线和彼此的重量旋转。 提供驱动装置，用于以选定的速度围绕旋转轴线旋转每个重量，以产生相对于和衰减具有所选频率的转子引起的振动的振荡剪切力。 垂直取向的振动衰减器被配置为抵抗和衰减垂直的转子诱导的振荡力，否则其将沿着转子桅杆向下垂直移动并进入机体。 振动衰减器，其具有围绕彼此偏移的分离轴线旋转的重物。

公开(公告)号：US20160264236A1

公开(公告)日：2016-09-15

申请号：US15066367

申请日：2016-03-10

申请人： AIRBUS HELICOPTERS

发明人： Julien HOCQUETTE

IPC分类号： B64C27/00

CPC分类号： B64C27/001 ,  B64C2027/004 ,  B64C2027/005

摘要： An antivibration suspension system of an aircraft, the antivibration suspension system comprising a lever and an oscillating mass. The antivibration suspension system comprises a mechanical motion amplifier device interposed between the lever and the oscillating mass, the motion amplifier device being provided both with a mechanical inlet constrained to move in rotation with the lever about a control axis and with a mechanical outlet driving rotary movement of the oscillating mass.

摘要翻译： 一种飞机的防振悬挂系统，该防振悬架系统包括杠杆和振动块。 防振悬挂系统包括插入在杠杆和振荡块之间的机械运动放大器装置，运动放大器装置设置有机械入口，该机械入口被限制为围绕控制轴线与杆一起旋转移动，并且机械出口驱动旋转运动 的振荡质量。

公开(公告)号：US09284048B2

公开(公告)日：2016-03-15

申请号：US14053061

申请日：2013-10-14

申请人： Sikorsky Aircraft Corporation

发明人： Matthew Harrigan

IPC分类号： B64C27/00 ,  B64F5/00 ,  F16F1/00

CPC分类号： B64C27/001 ,  B64C2027/004 ,  B64D45/00 ,  B64D2045/0085 ,  F16F1/00 ,  F16F15/002

摘要： According to one aspect, a controller, including a processor, sets an initial vibration frequency to be applied to an airframe. The controller commands one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency. The controller determines a vibration response of the airframe at the initial vibration frequency using sensors. The controller sweeps through a range of vibration frequencies to be applied to the airframe. The one or more force generators are commanded to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies. The controller determines a range of vibration responses of the airframe over the range of vibration frequencies using the sensors. A global stiffness of the airframe is determined based on the vibration response and the range of vibration responses. The controller reports results of the determined global stiffness of the airframe.

摘要翻译： 根据一个方面，包括处理器的控制器设置要施加到机身的初始振动频率。 控制器命令一个或多个力发生器以初始振动频率向机身施加振动载荷。 控制器使用传感器确定机身在初始振动频率下的振动响应。 控制器扫过一系列振动频率以应用于机身。 命令一个或多个力发生器在振动频率的范围内向机身施加多个振动载荷。 控制器使用传感器在振动频率的范围内确定机身的振动响应范围。 基于振动响应和振动响应的范围确定机身的全局刚度。 控制器报告所确定的机身的全局刚度的结果。

公开(公告)号：US09212722B2

公开(公告)日：2015-12-15

申请号：US13581192

申请日：2011-02-22

申请人： Yuji Yoshizaki ,  Hiroshi Ito ,  Hidetoshi Suzuki

发明人： Yuji Yoshizaki ,  Hiroshi Ito ,  Hidetoshi Suzuki

IPC分类号： H02K33/00 ,  H02P1/00 ,  H02P3/00 ,  H02P5/00 ,  F16F15/02 ,  B64C27/00 ,  F16F15/00 ,  H01L41/04 ,  H01L41/09

CPC分类号： F16F15/02 ,  B64C27/001 ,  B64C2027/004 ,  F16F15/005 ,  H01L41/042 ,  H01L41/09

摘要： A vibration reduction apparatus includes an actuator applying a force to a beam supporting a cabin so as to bend the beam, an acceleration sensor measuring the acceleration of the cabin, and a controller controlling the actuator based on the measured acceleration. When a vibration containing a plurality of vibration components is transmitted to the cabin via the beam, the vibration reduction apparatus thus structured reduces the vibration more certainly by applying a bending load to the beam so that the bending load caused by the vibration is cancelled. This provides damping of the cabin more certainly.

摘要翻译： 减振装置包括致动器，其对支撑舱室的梁施加力，以使梁弯曲，加速度传感器测量舱室的加速度;以及控制器，其基于所测量的加速度来控制致动器。 当通过梁将包含多个振动部件的振动传递到机舱时，由此构造的减振装置通过向梁施加弯曲载荷来更确定地减少振动，从而消除由振动引起的弯曲载荷。 这更可靠地提供了客舱的阻尼。