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71. 发明专利

JP2008524076A Sound absorption system in the interior trim panel system of the aircraft 有权
公开(公告)号：JP2008524076A
公开(公告)日：2008-07-10
申请号：JP2007548276
申请日：2005-12-12
申请人：シコルスキーエアクラフトコーポレイションSikorsky Aircraft Corporation
发明人：ドロースト，スチュアート，ケー． , フォルシエ，ジャレド，ルチアーノ
IPC分类号： B64C1/40
CPC分类号： B64C1/066 , B64C1/40
摘要：吸音トリムパネルが、複合コア、分離層、質量バリア層、を含む。質量バリア層が、柔軟領域の柔軟性を保持しつつ分離層を介して複合コアに接触することを確実にすることにより、従来の構造よりも大きなダンピングを実現する。

72. 发明申请

US20190015969A1 LOCATING POSITIONS ON COMPONENTS 审中-公开
公开(公告)号：US20190015969A1
公开(公告)日：2019-01-17
申请号：US15748737
申请日：2016-07-25
申请人： Sikorsky Aircraft Corporation
发明人： Nathan Doane
IPC分类号： B25H7/04 , B25H7/02
摘要： A method of locating position on a component includes engaging a template with a component and marking a location on the component using marking features of the template. Marking a location can include marking a plurality of locations on the component using a plurality of respective marking features of the template. Each marking feature of the template can include a corner formed where at least two edges meet on the template. Marking each respective location on the component can include marking two line segments that cross at an intersection point, wherein the two line segments follow the edges of the template at each respective corner, to mark the respective location on the component at the intersection of the two respective line segments. For example, marking each location can include marking a center point location for a strain gage, as well as the horizontal and vertical orientation.

73. 发明申请

WO2019066800A1 USE OF FIBER OPTIC STRAIN SENSORS TO MONITOR FASTENER DAMAGE IN STRUCTURES 审中-公开
公开(公告)号：WO2019066800A1
公开(公告)日：2019-04-04
申请号：PCT/US2017/053666
申请日：2017-09-27
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SARLASHKAR, Avinash V. , MEYER, Theodore S. , HARRIGAN, Matthew P.
IPC分类号： G01L1/24
CPC分类号： G01M5/0033 , F16B31/02 , G01L1/24 , G01M5/0091
摘要： A fastener health monitoring system includes a structure including a first component and a second component, one or more fasteners securing the first component to the second component, and an optical fiber arranged adjacent to the one or more fasteners. The fiber is configured to detect strain on the structure from the one or more fasteners. Strain patterns are derivable from sensed data from the optical fiber, and any deviation in strain value greater than a threshold value at a particular fiber position along the optical fiber is indicative of a missing, damaged, or loosened fastener amongst the one or more of fasteners corresponding to that particular fiber position.

74. 发明申请

WO2017069825A2 ROTORCRAFT STRUCTURAL FAULT-DETECTION AND ISOLATION USING VIRTUAL MONITORING OF LOADS 审中-公开
标题翻译：利用载荷虚拟监测的旋转机构结构故障检测与隔离
公开(公告)号：WO2017069825A2
公开(公告)日：2017-04-27
申请号：PCT/US2016/044187
申请日：2016-07-27
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ISOM, Joshua D. , DAVIS, Mark W. , CYCON, James Peter
IPC分类号： G06F19/00
CPC分类号： G07C5/0825 , B64C27/32 , B64D2045/0085 , F02C3/10 , G01H1/006
摘要： A system, method, and computer program for detecting and isolating structural faults is provided. To detect and isolate structural faults, a plurality of sensed features that corresponds to sensor data from the monitoring sub-system and a plurality of estimated features that corresponds to the plurality of sensed features can be generated. Further, the plurality of sensed features and the plurality of estimated features can be compared to produce a plurality of residuals. From the plurality of residuals, at least one structural fault within the vehicle are determined and isolated for further use of maintenance decision support.
摘要翻译：提供了一种用于检测和隔离结构性故障的系统，方法和计算机程序。为了检测和隔离结构性故障，可以生成与来自监测子系统的传感器数据相对应的多个感测特征以及与多个感测特征相对应的多个估计特征。此外，可以比较多个感测特征和多个估计特征以产生多个残差。从多个残差中确定并隔离车辆内的至少一个结构故障，以进一步使用维护决策支持。

75. 发明申请

WO2017015016A1 STRUCTURE REINFORCEMENT WITH POLYMER MATRIX COMPOSITE 审中-公开
标题翻译：结构加固与聚合物基体复合材料
公开(公告)号：WO2017015016A1
公开(公告)日：2017-01-26
申请号：PCT/US2016/042031
申请日：2016-07-13
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ZHAO, Wenping , CHAUDHRY, Zaffir A. , TONI, Darryl Mark , KUMMER, Peter
IPC分类号： B32B15/08 , B32B37/22 , E04B1/24 , E04C3/29 , E04C3/36
CPC分类号： B32B15/08 , B29C73/10 , B29C73/14 , B64F5/45 , E04C3/29 , E04C5/07
摘要： A structural reinforcement member is provided to be affixable to a metallic member. The metallic member defines a stress concentration section at which the metallic member is subject to loading in at least one direction such that stress is generated at the stress concentration section in at least one corresponding principal stress direction. The structural reinforcement member includes a polymer matrix composite (PMC) patch element and a bondline. The PMC patch element includes fibers suspended within a polymer matrix. The bondline is disposed to affix the PMC patch element to a surface of the metallic member at the stress concentration section such that the fibers extend along the principal stress direction.
摘要翻译：提供结构加强构件以可固定到金属构件。金属构件限定应力集中部分，金属构件在至少一个方向上承受载荷，使得在至少一个对应的主应力方向上在应力集中部分处产生应力。结构加强件包括聚合物基质复合（PMC）贴片元件和粘结线。 PMC贴片元件包括悬浮在聚合物基质内的纤维。粘合线设置成在应力集中部分处将PMC贴片元件贴合到金属构件的表面，使得纤维沿主应力方向延伸。

76. 发明申请

WO2017011063A1 CLEARANCE SENSOR SYSTEM 审中-公开
标题翻译：透明传感器系统
公开(公告)号：WO2017011063A1
公开(公告)日：2017-01-19
申请号：PCT/US2016/031630
申请日：2016-05-10
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： LESPERANCE, Jesse J. , GANDIA, Andrew , ZYGMANT, Thomas R. , VISINSKI, Nicholas Charles
IPC分类号： B25J9/00 , B65G69/00
CPC分类号： G05D3/00 , B64C1/22 , B64D5/00 , B64D9/00 , G01B21/16
摘要： A clearance sensor system is provided for use in moving first and second articles and includes a driving element disposed to drive and manipulate the first article relative to the second article, a plurality of sensors arrayed about at least the second article to generate real-time readings of physical separation of the first and second articles and a controller operably coupled to the driving element and the plurality of sensors. The controller is configured to facilitate an execution of real-time or quasi-dynamic control of a driving of the first article by the driving element in accordance with the readings of the physical separation between the first and second articles provided by the plurality of sensors, and a post-processing of data relating to the real-time or quasi-dynamic control of the driving and the manipulation of the first article by the driving element.
摘要翻译：提供了用于移动第一和第二物品的间隙传感器系统，并且包括设置成相对于第二物品驱动和操纵第一物品的驱动元件，围绕至少第二物品排列的多个传感器以产生实时读数所述第一和第二物品的物理分离以及可操作地耦合到所述驱动元件和所述多个传感器的控制器。控制器被配置为便于根据由多个传感器提供的第一和第二物品之间的物理分离的读数来促进由驱动元件驱动第一物品的实时或准动态控制，以及与通过驱动元件对第一物品的驾驶和操纵的实时或准动态控制有关的数据的后处理。

77. 发明申请

WO2016205472A2 CRASHWORTHY WHEELCHAIR ASSEMBLIES 审中-公开
公开(公告)号：WO2016205472A2
公开(公告)日：2016-12-22
申请号：PCT/US2016/037808
申请日：2016-06-16
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： GRAMPE, Tony , DAVIES, Matthew
IPC分类号： A61G5/10
CPC分类号： A61G3/0808 , A61G5/10 , A61G5/1081 , A61G2220/10 , B64D11/06 , B64D11/0696
摘要： A seat base assembly for a wheelchair includes a dock configured to be mounted to a vehicle frame. An attenuating mechanism is operatively connected to the dock to absorb impact between the vehicle frame and a wheelchair. An interface assembly is operatively connected to the attenuating mechanism to connect a wheelchair to the attenuating mechanism. A crashworthy wheelchair includes a seat having arm rests and a seat back extending therefrom. Front wheels and back wheels are operatively connected to the seat. Each arm rest includes a downward opening slot configured to accommodate a respective one of the back wheels during a negative G event. The wheelchair can include a hook extending down ward from the seat to engage with a respective mating portion of the seat base assembly.
摘要翻译：用于轮椅的座椅底座组件包括被构造成安装到车架上的基座。衰减机构可操作地连接到码头以吸收车架和轮椅之间的冲击。接口组件可操作地连接到衰减机构以将轮椅连接到衰减机构。防撞轮椅包括具有扶手的座椅和从其延伸的座椅靠背。前轮和后轮可操作地连接到座椅。每个扶手包括向下开口槽，其构造成在负G事件期间容纳相应的一个后轮。轮椅可以包括从座椅向下延伸的钩子，以与座椅基座组件的相应配合部分接合。

78. 发明申请

WO2016201079A1 TENSION TORSION STRAP 审中-公开
标题翻译：张力扭曲带
公开(公告)号：WO2016201079A1
公开(公告)日：2016-12-15
申请号：PCT/US2016/036653
申请日：2016-06-09
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： DARROW, David A. , WALDO, Ron William , RICHARDS, Joshua , HAYDEL, Kristopher Michael , HALCOM, Lance
IPC分类号： B64C27/48 , B64C27/473 , B64C27/46
CPC分类号： B64C27/48 , B64C27/10 , B64C27/33
摘要： A tension torsion strap by which a blade is connectable with a hub of a propulsor is provided. The tension torsion strap includes an elongate body formed to define attachment features at opposite ends thereof, the attachment features being connectable to the blade at one of the opposite ends and to the hub at the other of the opposite ends, fibrous materials extending along the elongate body and around the attachment features and pretension flanges elastically interposable between the hub and the elongate body. The pretension flanges are configured to maintain pretension in the fibrous materials above a predefined pretension level when the attachment features are connected to the blade and the hub.
摘要翻译：提供了一个张力扭力带，通过该张力扭力带，刀片可与推进器的轮毂连接。张力扭力带包括细长体，其形成为在其相对端部处限定附接特征，附接特征可在相对端中的一个处连接到叶片，并且在另一个相对端处连接到轮毂，纤维材料沿细长本体和围绕附接特征和预紧力凸缘弹性地相对于轮毂和细长体之间。预紧凸缘被构造成当附接特征连接到叶片和轮毂时，将纤维材料中的预张力保持在预定的预紧水平以上。

79. 发明申请

WO2016191166A1 SYSTEMS AND METHODS TO ASSESS CORROSION RISK 审中-公开
标题翻译：评估腐蚀风险的系统和方法
公开(公告)号：WO2016191166A1
公开(公告)日：2016-12-01
申请号：PCT/US2016/033021
申请日：2016-05-18
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BROOKHART, Andrew , DAVIS, Mark, W. , JAWOROWSKI, Mark, R.
IPC分类号： G01M99/00 , G01N17/04 , G01N21/95 , G06F17/40 , G06Q90/00
CPC分类号： G01N17/04 , B32B2605/18 , G01N21/95 , G06Q10/20
摘要： A method of assessing airframe corrosion risk includes determining a component corrosion stress based on data from at least one of a corrosivity sensor, an aircraft exposure history, a climate database, or an aircraft configuration. The method includes generating a component corrosion risk based on the determined component corrosion stress. An accumulated component corrosion risk is calculated based on the component corrosion risk and a historical component corrosion risk. An airframe corrosion risk is determined based on the accumulated component corrosion risk.
摘要翻译：一种评估机身腐蚀风险的方法包括基于来自腐蚀性传感器，飞机暴露历史，气候数据库或飞行器构造中的至少一个的数据来确定部件腐蚀应力。该方法包括基于确定的部件腐蚀应力产生部件腐蚀风险。积累的成分腐蚀风险是根据组分腐蚀风险和历史成分腐蚀风险计算的。基于积累的部件腐蚀风险确定机身腐蚀风险。

80. 发明申请

WO2016178736A1 SYSTEM AND METHOD FOR CALCULATING REMAINING USEFUL LIFE OF A COMPONENT 审中-公开
标题翻译：用于计算组件的剩余有用寿命的系统和方法
公开(公告)号：WO2016178736A1
公开(公告)日：2016-11-10
申请号：PCT/US2016/020636
申请日：2016-03-03
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SHELDON, Jeremy , KASPER, David , ARGENNA, Garrett
IPC分类号： G01D3/08 , G05B23/02
CPC分类号： G06F17/5009 , B64D45/00 , B64D2045/0085 , G05B23/0283 , G06Q10/20 , G07C5/0808
摘要： A system and method for determining a remaining useful life of a component, includes providing a usage and configuration information associated with the component, determining if a preexisting spall condition exists for the component, executing a spall initiation model for the component if the preexisting spall condition does not exist, wherein the spall initiation model provides a spall initiation life associated with the component by analyzing the usage and configuration information, executing a spall propagation model for the component, wherein the spall propagation model provides a spall propagation life associated with the component by analyzing the usage and configuration information, and providing a remaining useful life by integrating the spall initiation life and the spall propagation life.
摘要翻译：用于确定组件的剩余使用寿命的系统和方法包括提供与组件相关联的使用和配置信息，确定是否存在针对组件的预先存在的剥离条件，如果预先存在的剥离条件执行组件的剥离启动模型其中所述剥落启动模型通过分析所述使用和配置信息来提供与所述组件相关联的剥离启动寿命，对所述组件执行散布传播模型，其中所述散布传播模型通过以下方式提供与所述组件相关联的散布传播寿命：分析使用情况和配置信息，并通过集成散布引发寿命和剥离传播寿命来提供剩余的使用寿命。

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