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公开(公告)号：US20130207327A1
公开(公告)日：2013-08-15
申请号：US13813048
申请日：2011-07-28
Applicant: Marin Besliu
Inventor： Marin Besliu
CPC classification number: B64C25/505 , F16F9/065 , F16F9/325 , F16F13/007
Abstract: A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator (40) having an internal fluid volume that is significantly more important than a fluid volume expelled from the body of the shimmy damper when its piston moves fore and aft. The shimmy damper also includes a hydraulic manifold (30) arranged between the body and the hydraulic compensator and defining a transfer channel between chambers in the piston that is connected to the hydraulic compensator. The manifold receives interchangeable hydraulic cartridge-type valves (CV1,RV1;CV2,RV2) for metering the fluid flowing from the chambers to the transfer channel, and allows the fluid to freely enter the chambers from the transfer channel. The present shimmy damper is therefore much less sensitive to oil temperature variation under intense shimmy.
Abstract translation: 一种液压振动阻尼器，其解决了几种已知的振动阻尼器中的缺点，例如取决于油温变化的阻尼特性。 所公开的振动阻尼器包括液压补偿器（40），该液压补偿器具有内部流体体积，当其活塞前后移动时，该流体体积比从振动阻尼器的主体排出的流体体积显着更重要。 振动阻尼器还包括设置在主体和液压补偿器之间的液压歧管（30），并且在连接到液压补偿器的活塞中的腔室之间限定了传送通道。 歧管接收可互换的液压盒式阀（CV1，RV1; CV2，RV2），用于计量从腔室流到传送通道的流体，并允许流体从传送通道自由进入腔室。 因此，目前的振动阻尼器在强烈的振动下对油温变化的敏感性要小得多。
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公开(公告)号：US20120292443A1
公开(公告)日：2012-11-22
申请号：US13534134
申请日：2012-06-27
Applicant: Steve AMBERG
Inventor： Steve AMBERG
IPC: B64C25/16
Abstract: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.
Abstract translation: 本发明提供一种用于打开和关闭飞机起落架舱门的双钩门机构。
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公开(公告)号：US20120280564A1
公开(公告)日：2012-11-08
申请号：US13549838
申请日：2012-07-16
Applicant: Chris BROOKFIELD
Inventor： Chris BROOKFIELD
IPC: B64D31/14
Abstract: Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.
Abstract translation: 公开了一种用于选择性地操作至少一个飞行器装置的蓄电池。 蓄电器包括用于存储电能的超电容器阵列，其可以稍后用于为飞行器装置供电。 存储的电能也可以用作紧急备用电源。 电能的分配由配电控制器控制。 蓄电池可以由飞机上的电源充电，或者可以由外部电源预充电。
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公开(公告)号：US08267351B2
公开(公告)日：2012-09-18
申请号：US12630465
申请日：2009-12-03
Applicant: Chris Brookfield
Inventor： Chris Brookfield
IPC: B64C25/14
CPC classification number: B64C25/16
Abstract: The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door.
Abstract translation: 本发明提供了一种飞机着陆舱门机构，其包括使用用于打开和关闭着陆舱门的滚轮槽机构。
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公开(公告)号：US08181532B2
公开(公告)日：2012-05-22
申请号：US11573218
申请日：2005-08-30
Applicant: Robert Kyle Schmidt , Nader Abu El-samid
Inventor： Robert Kyle Schmidt , Nader Abu El-samid
IPC: G01L1/24
CPC classification number: B64C25/00 , B64D2045/008 , G01B11/16 , G01B11/306 , G01G3/125 , G01G19/07 , G01M11/08
Abstract: The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at least one light position sensing device connected to the axle. The sensing device is located relative to the light beam emitting device for receiving at least one light beam from the light beam emitting device thereon and is operable to calculate the position of the light beam received on its surface.
Abstract translation: 本发明提供一种用于安装在轴上的结构偏转和载荷测量装置。 该装置包括连接到该轴并能够发射至少一个光束的至少一个光束发射装置和连接到该轴的至少一个光位置传感装置。 感测装置相对于光束发射装置定位，用于从其上的光束发射装置接收至少一个光束，并且可操作以计算在其表面上接收的光束的位置。
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Patent Agency Ranking
公开(公告)号：US07845220B2
公开(公告)日：2010-12-07
申请号：US11844900
申请日：2007-08-24
Applicant: R. Kyle Schmidt , Simon Hou
Inventor： R. Kyle Schmidt , Simon Hou
CPC classification number: F17C13/04 , F16F9/3264 , F16F9/3292 , F16F9/43 , F16F2230/0047 , F16F2230/06 , F16F2230/08 , F16F2230/24 , F17C2250/043 , F17C2270/0189 , Y10T29/49716
Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.
Abstract translation: 本发明是允许测量飞行器起落架冲击支柱内的压力的装置。 通过将小的压力感测装置集成到部件的杆中来改变充气阀，使得活动隔膜受到带电容器内的压力。 来自压力感测装置的电线连接到杆的孔中的插座或连接器，使得相应的电插座可以配合用于进行测量。 内部容器被设计成使得空气或油的流动不被过大的阻碍，并且正常的维修工具不会妨碍容器。
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7.发明申请公开(公告)号：US20090293624A1
公开(公告)日：2009-12-03
申请号：US11844900
申请日：2007-08-24
Applicant: R. Kyle SCHMIDT , Simon Hou
Inventor： R. Kyle SCHMIDT , Simon Hou
CPC classification number: F17C13/04 , F16F9/3264 , F16F9/3292 , F16F9/43 , F16F2230/0047 , F16F2230/06 , F16F2230/08 , F16F2230/24 , F17C2250/043 , F17C2270/0189 , Y10T29/49716
Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.
Abstract translation: 本发明是允许测量飞行器起落架冲击支柱内的压力的装置。 通过将小的压力感测装置集成到部件的杆中来改变充气阀，使得活动隔膜受到带电容器内的压力。 来自压力感测装置的电线连接到杆的孔中的插座或连接器，使得相应的电插座可以配合用于进行测量。 内部容器被设计成使得空气或油的流动不被过大的阻碍，并且正常的维修工具不会妨碍容器。
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公开(公告)号：US20080217107A1
公开(公告)日：2008-09-11
申请号：US12024631
申请日：2008-02-01
Applicant: R. Kyle SCHMIDT
Inventor： R. Kyle SCHMIDT
CPC classification number: B64C25/18 , Y10T403/255
Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.
Abstract translation: 本发明提供一种销组件，该销组件是自润滑的，并且包括销，销插入件，其被容纳在销内和一定量的润滑剂。 本发明还提供一种用于销钉的插入件，其可以用在包含自动润滑分配机构的销接头中。
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公开(公告)号：US20170121015A1
公开(公告)日：2017-05-04
申请号：US14932655
申请日：2015-11-04
Applicant: James Yuan-Chern Ning
Inventor： James Yuan-Chern Ning
CPC classification number: B64C25/505 , F16F7/112
Abstract: A damper for an aircraft landing gear includes a housing with an internal cavity. A weight is slidingly disposed within the cavity and positioned between and engages a first pneumatic spring and a second pneumatic spring. The shimmy damper includes at least one mounting feature to fixedly mount the housing to a component of the aircraft landing gear.
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公开(公告)号：US20140252210A1
公开(公告)日：2014-09-11
申请号：US13789779
申请日：2013-03-08
Applicant: MESSIER-DOWTY INC.
Inventor： Kyle Schmidt
IPC: G01B11/16
CPC classification number: H03K17/945 , G01K11/32 , G01V3/08 , H03K2217/95
Abstract: A proximity sensor for detecting non-contact detection of a target using a fibre optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fibre that has an optic fibre strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fibre strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fibre, such as a fibre Bragg grating. The proximity sensor can include a second fibre optic sensor that is sensitive to temperature or a second fibre optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor. The processor compares frequency information from the proximity sensor to a threshold to determine whether a target is in proximity to its corresponding proximity sensor.
Abstract translation: 公开了一种用于使用光纤应变传感器和用于操作多个这种接近传感器的系统来检测目标的非接触检测的接近传感器。 接近传感器包括具有光纤应变传感器的光纤，光纤应变传感器耦合到响应于目标移动的质量块。 质量可以是当铁质靶位于磁体的磁场内时使磁体移动并施加应变到光纤应变传感器的磁体。 光学应变传感器可以包括光纤的折射率的周期性变化，例如光纤布拉格光栅。 接近传感器可以包括对温度敏感的第二光纤传感器或耦合到与第一磁体相对操作的第二磁体的第二光纤应变传感器。 耦合多个接近传感器的系统可以包括具有光功率源和检测器的询问器，每个耦合到处理器。 处理器将来自接近传感器的频率信息与阈值进行比较，以确定目标是否在其相应的接近传感器附近。
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