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1. 发明申请

WO2017048627A1 AIRCRAFT SUPPORT STRUCTURES, SYSTEMS, AND METHODS 审中-公开
标题翻译：飞机支援结构，系统和方法
公开(公告)号：WO2017048627A1
公开(公告)日：2017-03-23
申请号：PCT/US2016/051279
申请日：2016-09-12
申请人： LORD CORPORATION
发明人： BOZON, Benjamin , KURSNER, Alexandre , NARBON, Baptiste , ZAMEROSKI, Daniel
IPC分类号： B64C27/00 , B64D27/26 , F16F9/56 , B64D13/00 , B64D41/00
CPC分类号： B64C27/001 , B64C2027/002 , B64D13/00 , B64D27/26 , B64D41/00 , B64D2041/002 , F16F2230/0041 , Y02T50/44
摘要： Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P1) that is configured to lock, automatically, an inner member (214) of the support with respect to an outer member (208) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.
摘要翻译：公开了飞机支撑结构，系统和方法。在一个实施例中，飞行器系统包括旋转部件和支撑旋转部件的支撑件（例如支柱）。支撑件包括锁定组件（P1），其被构造成相对于支撑件的外部构件（208）自动地锁定支撑件的内部构件（214），以响应于达到或超过预定的位移量，载荷，应力或旋转阈值。本文中的飞行器支撑结构，系统和方法利用自锁和自解锁支撑（例如支柱）来增加或减小支撑件的刚度。

2. 发明申请

WO2015160945A1 SYSTEMS AND METHODS FOR STRUCTURAL HEALTH MONITORING AND PROTECTION 审中-公开
标题翻译：用于结构健康监测和保护的系统和方法
公开(公告)号：WO2015160945A1
公开(公告)日：2015-10-22
申请号：PCT/US2015/025963
申请日：2015-04-15
申请人： LORD CORPORATION
发明人： BLACK, Paul , SWANSON, Douglas , PEDERSEN, Douglas, G. , JOLLY, Mark, R. , TOWNSEND, Christopher , CASSIDY, Ian
IPC分类号： G01M5/00 , B64C27/00
CPC分类号： B64C27/001 , B64C2027/002 , B64C2027/004 , B64C2027/005 , B64D45/00 , B64D2045/0085 , G01M5/0033 , G01M5/0066
摘要： Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.
摘要翻译：提供结构健康监测和保护系统和方法。系统和方法利用结构信息和/或增强的内置测试能力来检测可能对结构造成损害的故障模式。这里的系统和方法可以通过减轻一个或多个不正确的力来保护结构。该结构可以是飞行器，旋转飞行器或受到振动和接受这些振动的抵消的任何其它物理结构。

3. 发明申请

WO1996020107A1 ANTI-VIBRATION SUSPENSION DEVICE FOR A HELICOPTER ROTOR 审中-公开
标题翻译：用于直升机转子的抗振动悬挂装置
公开(公告)号：WO1996020107A1
公开(公告)日：1996-07-04
申请号：PCT/FR1995001728
申请日：1995-12-22
申请人： EUROCOPTER FRANCE , MOUILLE, René, Louis
发明人： EUROCOPTER FRANCE
IPC分类号： B64C27/00
CPC分类号： F16F15/06 , B64C27/001 , B64C2027/002 , F16F15/02
摘要： A suspension device including two parallel connecting rods (14) joining the base (5b) of the gearbox to the fuselage (6), said rods being hinged (15) to side supports (16) fastened to opposite sides of the base (5b), and extending on one side of the gearbox up to where they are joined (19) to structural supports (20) of the fuselage (6). Resilient linkages (17) provide suspension at least in a direction perpendicular to the connecting rods (14). In an alternative embodiment, the connecting rods (14) are hingedly connected to the fuselage (6) via a flexible crossbar optionally provided with a central flapping weight, or via transverse levers hinged together via a central hinge or hingedly connected to the structure. The device is useful for one- or two-way suspension, focal point suspension and optionally non-resonant suspension in helicopter main rotors.
摘要翻译：一种悬挂装置，包括将所述齿轮箱的底座（5b）连接到所述机身（6）的两个平行的连接杆（14），所述杆铰接（15）到紧固到所述基座（5b）的相对侧的侧支撑件（16）并且在所述齿轮箱的一侧延伸到它们被连接到所述机身（6）的结构支撑件（20）的位置。弹性连杆（17）至少在垂直于连杆（14）的方向上提供悬挂。在替代实施例中，连接杆（14）通过柔性横杆铰接地连接到机身（6），柔性横杆可选地设置有中心扑动重物，或通过经由中心铰链铰接在一起或铰接地连接到该结构的横向杆。该装置可用于直升机主转子中的一次或双向悬架，焦点悬架和非共振悬架。

4. 发明申请

WO1991001229A1 HYDROSTATIC POWER TRANSFER SYSTEM 审中-公开
标题翻译：水力发电系统
公开(公告)号：WO1991001229A1
公开(公告)日：1991-02-07
申请号：PCT/US1990004042
申请日：1990-07-18
申请人： TOBIAS, Jaromir
IPC分类号： B60K17/356
CPC分类号： B60K17/10 , B60K6/12 , B64C2027/002 , Y02T10/6208
摘要： A hydrostatic power transfer system for transferring power from a rotating power input shaft (102) to a rotating output shaft (108) comprises a fluid pump (103) for supplying pressurized fluid to a pump outlet. A pressure accumulator (105) is disposed downstream of the pump and has an inlet for accepting pressurized fluid from the pump outlet and an outlet for discharging fluid under pressure from the accumulator. The accumulator includes two chambers (105B and 105C) and a pressure transmissive member (105A) separating the two chambers. The pressurized fluid from the pump is supplied to one (105C) of the two chambers and the other chamber (105B) includes a pressurized gas which acts against the pressurized fluid in the one chamber via the pressure transmissive member for insulating the system against vibration transmission through the accumulator. Controller (110) provides continuous, rapid adjustments to changing conditions along the system to assure a smooth controlled drive of motor (107).

5. 发明申请

WO2016057215A1 ANTI-VIBRATION MOMENT GENERATING AIRCRAFT ACTUATION SYSTEM 审中-公开
标题翻译：抗振动发电机制动系统
公开(公告)号：WO2016057215A1
公开(公告)日：2016-04-14
申请号：PCT/US2015/051576
申请日：2015-09-23
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HUNTER, David H. , WELSH, William A. , BASKIN, Bryan Kenneth , BUTLER, Chris Paul
IPC分类号： B64C27/00 , B64C27/08 , B64C27/51
CPC分类号： B64C27/001 , B64C27/10 , B64C27/12 , B64C2027/002 , B64C2027/004
摘要： An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.
摘要翻译：提供飞机并包括机身，发动机，由发动机驱动的驱动部分，转子装置，其包括相对于机身可转动的转子和整流罩，齿轮箱被设置成将旋转能量从驱动部分传递到转子，以驱动转子相对于机身旋转并产生转子旋转振动，齿轮箱设置在机身上的支撑构件和包括设置在整流罩上的致动元件的致动系统，致动系统被配置为产生使用设置在整流罩上的致动元件来抵抗转子旋转振动的抗振动力矩。

6. 发明申请

WO2016001901A1 HELICOPTER WITH NOISE AND VIBRATION DAMPING TRANSMISSION MOUNTING 审中-公开
标题翻译：具有噪声和振动阻尼传动装置的直升机
公开(公告)号：WO2016001901A1
公开(公告)日：2016-01-07
申请号：PCT/IB2015/055045
申请日：2015-07-03
申请人： AGUSTAWESTLAND S.P.A.
发明人： BOTTASSO, Luigi Maria , GHIRINGHELLI, Gian Luca , PERAZZOLO, Alessandro , CENEDESE, Fausto
IPC分类号： B64C27/00 , B64C27/12
CPC分类号： B64C27/001 , B64C27/12 , B64C27/82 , B64C2027/002
摘要： A helicopter (1) is described that comprises: a rotor (3); a fuselage (2); a drive transmission unit (7) operatively connected to the rotor (3); a support body (14), which supports the transmission unit (7); and constraining means (21) interposed between the support body (14) and the fuselage (2); the constraining means (21) in turn comprise a crosspiece (21) connected in a fixed manner with respect to the support body (14) and having a first lying plane (P); the crosspiece (21) is formed in part by a metallic material and in part by a visco-elastic material.
摘要翻译：一种直升机（1），其包括：转子（3）; 机身（2）; 可操作地连接到转子（3）的驱动传动单元（7）; 支撑所述传动单元（7）的支撑体（14）; 以及插入在所述支撑体（14）和所述机身（2）之间的约束装置（21）。约束装置（21）又包括相对于支撑体（14）以固定方式连接并且具有第一躺平面（P）的横档（21）; 横档（21）部分地由金属材料形成，部分地由粘弹性材料形成。

7. 发明申请

WO2013011264A1 A SYSTEM AND METHOD FOR REDUCING THE TRANSMISSION OF VIBRATION FROM A FIRST VIBRATING BODY TO A SECOND BODY 审中-公开
标题翻译：用于减少从第一振动体向第二体的振动传递的系统和方法
公开(公告)号：WO2013011264A1
公开(公告)日：2013-01-24
申请号：PCT/GB2012/050670
申请日：2012-03-26
申请人： AGUSTAWESTLAND LIMITED , PLUMMER, Andrew , COURT, Peter , HENDERSON, Jean-Paul , JOHNSTON, Nigel
发明人： PLUMMER, Andrew , COURT, Peter , HENDERSON, Jean-Paul , JOHNSTON, Nigel
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C2027/002
摘要： A system for reducing the transmission of vibration from a first vibrating body to a second body, the system having a first part connected to the first vibrating body, a second part connected to the second body and an electro-hydrostatic actuator connected to the first and second parts, the electro-hydrostatic actuator being operable to continuously oscillate the first and second parts 10 relative to each other at a frequency substantially corresponding to the frequency of vibration of the first vibrating body.
摘要翻译：一种用于减少振动从第一振动体传递到第二体的系统，该系统具有连接到第一振动体的第一部分，连接到第二主体的第二部分和连接到第一主体的静电静电致动器第二部分，静电静电致动器可操作以以基本上对应于第一振动体的振动频率的频率相对于彼此连续振荡第一和第二部分10。

8. 发明申请

WO2008100246A2 SELF-RETAINING ANTI-ROTATION CLIP 审中-公开
标题翻译：自保持防旋转夹
公开(公告)号：WO2008100246A2
公开(公告)日：2008-08-21
申请号：PCT/US2007/003597
申请日：2007-02-09
申请人： BELL HELICOPTER TEXTRON INC. , HALCOM, Lancer, D. , DAY, Clifton, B.
发明人： HALCOM, Lancer, D. , DAY, Clifton, B.
IPC分类号： F16C11/06
CPC分类号： F16C11/0614 , B64C2027/002 , Y10T403/32565 , Y10T403/32803 , Y10T403/32852 , Y10T403/32901 , Y10T403/32918
摘要： A self-retaining anti-rotation clip for a spherical-bearing rod end has two opposing spacer plates, each spacer plate having a curved edge portion for surrounding at least a portion of a ball of the rod end. A connector plate connects the spacer plates, such that the spacer plates are spaced from each other and generally parallel to each other. Retaining means are carried on the clip and adapted for retaining each spacer plate in a position generally adjacent one side of a body of the rod end, such that the spacer plates are free from interference with the ball of the rod end.
摘要翻译：用于球形支承杆端部的自固定防旋转夹具具有两个相对的间隔板，每个间隔板具有用于围绕杆端的球的至少一部分的弯曲边缘部分。连接板将间隔板连接，使得间隔板彼此间隔开且大致彼此平行。保持装置被承载在夹子上并且适于将每个隔板保持在大致邻近杆端主体的一侧的位置，使得间隔板不会与杆端的球干涉。

9. 发明申请

WO02084418A3 SYSTEM FOR COMPUTATIONALLY EFFICIENT ADAPTATION OF ACTIVE CONTROL OF SOUND OR VIBRATION 审中-公开
标题翻译：用于有效控制声音或振动的计算机系统
公开(公告)号：WO02084418A3
公开(公告)日：2003-03-20
申请号：PCT/US0205846
申请日：2002-02-27
申请人： SIKORSKY AIRCRAFT CORP
发明人： MACMARTIN DOUGLAS G , WELSH WILLIAM ARTHUR , FULLER JAMES W
IPC分类号： G05B5/01 , G05B13/04 , G05B23/02
CPC分类号： G05B13/042 , B64C2027/002 , G05B5/01
摘要： In a method for reducing sensed physical variables generating a plurality of control commands are generated at a control rate as a function of the sensed physical variables. An estimate of a relationship between the sensed physical variables and the control commands is also is used in generating the plurality of control commands. The estimate of the relationship is updated at an adaptation rate less than said control rate based upon a response by the sensed physical variables to the control commands.
摘要翻译：在用于减少产生多个控制命令的感测物理变量的方法中，以控制率作为感测物理变量的函数产生。感测物理变量与控制命令之间的关系的估计也用于生成多个控制命令。基于感测到的物理变量对控制命令的响应，以小于所述控制速率的自适应速率更新关系的估计。

10. 发明申请

WO2017103837A1 DRONE A FAIBLE NIVEAU DE VIBRATION 审中-公开
标题翻译：无声振动水平
公开(公告)号：WO2017103837A1
公开(公告)日：2017-06-22
申请号：PCT/IB2016/057651
申请日：2016-12-15
申请人： EVODRONE , GARDIN, Arthur , ROQUE, Florent
发明人： GARDIN, Arthur , ROQUE, Florent
IPC分类号： B64C27/00 , B64C39/02
CPC分类号： B64C39/024 , B64C27/001 , B64C2027/002 , B64C2201/027 , B64C2201/127
摘要： Drone comprenant un fuselage et une pluralité de structures de logements (3) pour une pluralité de groupe motopropulseurs (4) la liaison mécanique entre chaque groupe motopropulseur (4) et chaque structure de logement (3) de groupe motopropulseur (4) comprenant : - une rotule (10) disposée dans l'axe de rotation du groupe motopropulseur (4), à l'opposé du rotor (6); - un élément de liaison souple (20), reliant le groupe motopropulseur (4) à la structure de logement (3) du groupe motopropulseur (4).
摘要翻译：无人驾驶飞机包括机身和多个飞行器; （3）用于多个壳体; （4）每个动力传动系（4）与每个传动系壳体结构（3）之间的机械连接包括： - 球形接头（10），其布置在所述动力传动系动力传动系（4），＆amp; 相反＆eacute; 转子（6）; - 柔性连接元件（20），其连接动力系统（4）动力传动系（4）的壳体结构（3）。

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