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81. 发明公开

EP3174706A2 METHOD OF MAKING A COMPOSITE ARTICLE 审中-公开
标题翻译：制作复合制品的方法
公开(公告)号：EP3174706A2
公开(公告)日：2017-06-07
申请号：EP15853467.7
申请日：2015-07-31
申请人： Sikorsky Aircraft Corporation
发明人： ALMS, Justin B. , AMIS, Eric J. , SANGIOVANNI, Joseph J. , SUN, Ellen Y. , NARDI, Aaron T.
IPC分类号： B32B5/02
CPC分类号： B29C66/742 , B29C66/721 , B32B5/02 , B32B5/22 , B32B5/26 , B32B7/12 , B32B15/08 , B32B15/20 , B32B2250/42 , B32B2255/02 , B32B2255/205 , B32B2260/021 , B32B2260/046 , B32B2262/0269 , B32B2262/10 , B32B2262/101 , B32B2262/103 , B32B2262/105 , B32B2262/106 , B32B2262/14 , B32B2307/202 , B32B2307/302 , B32B2307/306 , B32B2307/50 , B32B2307/554 , B32B2307/718 , B32B2605/00 , C23C24/04 , C23C28/00
摘要： A method of making a composite article involves first forming an intermediate substrate. The intermediate substrate can be formed from fibers and an uncured thermoset polymer composition followed by partial cure, or from fibers and an uncured thermoset polymer composition followed by cure of the thermoset polymer composition and deposition of a thermoplastic on the surface of the substrate, or from fibers and an uncured thermoset polymer composition followed by cure and exposure of the substrate to organic solvent, a plasticizer, moisture, and/or heat. The intermediate substrate prepared according to any of the above techniques is then subjected to cold gas spray deposition to deposit a metal layer onto the intermediate substrate. In the case where the substrate was formed by partially curing a thermoset polymer composition, the metal-coated partially-cured thermoset polymer substrate is then fully cured.
摘要翻译：制造复合制品的方法涉及首先形成中间基材。中间基材可以由纤维和未固化的热固性聚合物组合物接着部分固化而成，或者由纤维和未固化的热固性聚合物组合物形成，接着固化热固性聚合物组合物并在基材表面上沉积热塑性材料，纤维和未固化的热固性聚合物组合物，随后固化并将基材暴露于有机溶剂，增塑剂，湿气和/或热。然后将根据任何上述技术制备的中间基板进行冷气体喷射沉积以将金属层沉积到中间基板上。在通过部分固化热固性聚合物组合物形成基材的情况下，然后将金属涂覆的部分固化的热固性聚合物基材完全固化。

82. 发明授权

EP2333726B1 Virtual monitoring of aircraft fleet loads 失效
标题翻译：飞机机队负载的虚拟监控
公开(公告)号：EP2333726B1
公开(公告)日：2017-05-10
申请号：EP10251921.2
申请日：2010-11-12
申请人： Sikorsky Aircraft Corporation
发明人： Isom, Joshua D. , Cycon, James P. , Eller, Erez , Davis, Mark W.
IPC分类号： G05B23/02 , G06Q10/06 , G07C5/00 , G07C5/08
CPC分类号： G07C5/006 , G05B23/024 , G05B23/0283 , G06Q10/06311 , G07C5/008 , G07C5/0841

83. 发明公开

EP3149896A1 GROUP SCHEDULED SENSOR DATA ACQUISITION IN A WIRELESS SENSOR SYSTEM 有权
标题翻译： EINEM DRAHTLOSEN SENSORSYSTEM中的GRUPPENGEPLANTE SENSORDATENERFASSUNG
公开(公告)号：EP3149896A1
公开(公告)日：2017-04-05
申请号：EP15799670.3
申请日：2015-05-21
申请人： Sikorsky Aircraft Corporation
发明人： CORBIN, Scott Alan
IPC分类号： H04L12/28
CPC分类号： H04W4/08 , H04L67/12 , H04L67/325 , H04W4/38 , H04W56/0015 , H04W72/12 , H04W84/18
摘要： A wireless sensor system includes wireless sensor nodes, each including a sensor interface that interfaces with sensing circuitry, a wireless interface to communicate with a wireless access point, at least one processor, and memory. The memory has instructions stored thereon that, when executed by the at least one processor, cause the wireless sensor node to compare a group identifier received in a message at the wireless interface with a group identifier of the wireless sensor node. Based on determining that the group identifier received matches the wireless sensor node, a start time to trigger is set in the wireless sensor node according to a start time defined in the message. A local clock of the wireless sensor node is monitored. Based on determining that the local clock has reached the start time to trigger, sensor data are acquired through the sensor interface and transmitted on the wireless interface.
摘要翻译：无线传感器系统包括无线传感器节点，每个节点包括与感测电路接口的传感器接口，与无线接入点通信的无线接口，至少一个处理器和存储器。存储器具有存储在其上的指令，当由至少一个处理器执行时，无线传感器节点将在无线接口处的消息中接收到的组标识符与无线传感器节点的组标识符进行比较。基于确定接收到的组标识与无线传感器节点匹配，根据消息中定义的开始时间在无线传感器节点中设置触发开始时间。监视无线传感器节点的本地时钟。基于确定本地时钟已经到达触发的开始时间，传感器数据通过传感器接口获取并在无线接口上传输。

84. 发明公开

EP3140610A2 ROTOR SYSTEM STRUCTURAL FAULT ESTIMATION 审中-公开
标题翻译： ROTORSYSTEMSTRUKTURFEHLERSCHÄTZUNG
公开(公告)号：EP3140610A2
公开(公告)日：2017-03-15
申请号：EP15803583.2
申请日：2015-03-05
申请人： Sikorsky Aircraft Corporation
发明人： ISOM, Joshua D.
IPC分类号： G01B5/28
CPC分类号： B64C27/006 , G01L5/0009 , G01L5/133 , G01M5/0016 , G01M5/0041 , G05B23/0221 , G05B23/0224 , G07C5/085
摘要： One aspect is a structural fault estimation system for a rotor system. The structural fault estimation system includes a plurality of sensors operable to provide a plurality of measured rotor loads and motion of the rotor system. A rotor loads and motion estimator is operable to produce a plurality of estimated rotor loads and motion for the rotor system. A rotor fault estimator is operable to determine residual rotor loads and motion as a difference between the measured rotor loads and motion and the estimated rotor loads and motion, and estimate fault magnitudes for the rotor system using least squares relative to fault models and the residual rotor loads and motion. The structural fault estimation system can perform structural fault estimation in real-time on an aircraft while in operation.
摘要翻译：一个方面是用于转子系统的结构故障估计系统。结构故障估计系统包括可操作以提供多个测量的转子负载和转子系统的运动的多个传感器。转子负载和运动估计器可操作以产生用于转子系统的多个估计的转子负载和运动。转子故障估计器可操作以将剩余转子负载和运动确定为所测量的转子负载和运动与估计的转子负载和运动之间的差异，并且使用相对于故障模型的最小二乘法估算转子系统的故障量值，并且剩余转子负载和运动。结构故障估计系统可以在运行中对飞机进行实时的结构故障估计。

85. 发明公开

EP3137377A1 RADIALLY COMPLIANT QUILL SHAFT 有权
标题翻译：径向弹性体
公开(公告)号：EP3137377A1
公开(公告)日：2017-03-08
申请号：EP15785724.4
申请日：2015-04-22
申请人： Sikorsky Aircraft Corporation
发明人： GARCIA, Todd A. , BASKIN, Bryan Kenneth , DING, Huali , XU, Biqiang
IPC分类号： B64C27/12
摘要： A quill shaft which translates rotational energy between a gear and a drive shaft having a drive shaft spline includes a first leg having an inner spline which meshes with the drive shaft spline and a second leg concentric with the first leg and radially offset and separated from the first leg by a gap. The second leg includes an outer spline which meshes with the gear. The first leg is connected to the second leg at one end to allow for change to a gap size during while translating the rotational energy between the gear and a drive shaft.
摘要翻译：在齿轮和具有驱动轴花键的驱动轴之间平移旋转能量的套筒轴包括具有与驱动轴花键啮合的内花键和与第一腿同心的第二腿部的第一腿部，并且径向偏移并与第一腿部分离第一条腿差距。第二腿包括与齿轮啮合的外花键。第一腿在一端连接到第二腿，以允许在齿轮和驱动轴之间平移旋转能量的同时改变间隙尺寸。

86. 发明授权

EP1871665B1 DUAL-CHANNEL DEICING SYSTEM FOR A ROTARY WING AIRCRAFT 有权
标题翻译：旋翼式飞机的双通道处理系统
公开(公告)号：EP1871665B1
公开(公告)日：2017-03-08
申请号：EP06749001.1
申请日：2006-03-31
申请人： Sikorsky Aircraft Corporation
发明人： BUDD, Timothy, R. , DANIELE, Antonio, G. , EISENHAUER, Mark, P. , HOULIHAN, Michael , FLEMMING, Robert, J., Jr.
IPC分类号： B64C27/04 , B64D15/14 , B64D15/22 , H05B1/02
CPC分类号： B64D15/12 , B64C27/04 , B64D15/14 , B64D15/22 , H05B1/0236
摘要： A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.
摘要翻译：除冰系统包括双除冰系统组件以提供冗余除冰系统。系统的每个冗余部分通常包括控制器，大气数据计算机，冰速率控制器和冰速率探测器。控制器传送定义多个电脉冲串的加热循环，以顺序地向指定刀片组中的多个加热元件提供功率。每个电脉冲序列由元件接通时间，元件接通时间与该元件之间的零时间以及重复第一加热器元件的加热周期之间的断开时间来定义。元件导通时间是外部空气温度（OAT）的函数。关闭时间是液态水含量的函数。尾桨加热循环是主旋翼加热循环的更直接的形式，因为每个尾桨叶片同时被激活，并且每个尾桨叶片上仅有单个加热元件。

87. 发明授权

EP2829471B1 Swashplateless coaxial rotary wing aircraft 有权
标题翻译：无斜盘同轴旋翼飞机
公开(公告)号：EP2829471B1
公开(公告)日：2017-02-15
申请号：EP14177865.4
申请日：2014-07-21
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Weiner, Steven D. , Bourne, Frederick L.
IPC分类号： B64C27/10 , B64C27/72 , B64C27/32 , B64C27/12 , B64C27/82
CPC分类号： B64C27/80 , B64C27/10 , B64C27/12 , B64C27/32 , B64C27/72 , B64C2027/7216 , B64C2027/8236 , H02K99/10 , Y02T50/34

88. 发明公开

EP3126980A2 SYSTEM AND METHOD FOR IMPROVED HEALTH MANAGEMENT AND MAINTENANCE DECISION SUPPORT 审中-公开
标题翻译：系统和方法以改进决策支持健康管理与保护
公开(公告)号：EP3126980A2
公开(公告)日：2017-02-08
申请号：EP15811394.4
申请日：2015-04-02
申请人： Sikorsky Aircraft Corporation
发明人： BANDY, Isaac , CYCON, James P. , ROZAK, James N. , DAVIS, Mark W. , KACPRZYNSKI, Gregory J. , MACKOS, Nicholas A.
IPC分类号： G06F11/00
CPC分类号： G07C5/0808 , G06Q10/20 , G07C5/006 , G07C5/008 , G07C5/0816
摘要： A method of health management of a monitored system includes collecting component condition indicator data used to calculate a plurality of component health indicators. Component fault severity and potential failure modes are determined utilizing the component condition indicator data. The potential failure modes are ranked in order of likelihood to isolate the failure mode. A system of health management for monitored apparatus includes a fault severity module to derive a plurality of component health indicators from collected component condition indicator data, the plurality of component health indicators indicative of fault severity of a plurality of components. A fault isolation module separately derives a ranked listing of potential fault/failure modes utilizing the component condition indicator data. The system further includes a communication portion to which the plurality of component health indicators and the ranked listing of fault/failure modes are transmitted for review and/or action by cognizant personnel.
摘要翻译：被监视的系统的健康管理的一种方法，包括：收集用于计算部件的健康指标的多个分量条件指示符数据。部件故障严重性和潜在的失效模式是确定性的开采利用该部件状态指示器数据。潜在的故障模式都排在似然性的顺序以隔离故障模式。用于监视的装置的健康管理的一种系统包括一个故障严重性模块导出的从部件状态指示符数据，指示的部件的多个故障严重性的组件健康指标。多个收集的组件健康指标复数。故障隔离模块分别导出潜在故障/故障模式利用所述部件状态指示符数据的排序列表。该系统包括通信进一步帮助的组成部分卫生指标的多元性和故障/故障模式的排名上市是哪家审查和/或采取行动的人员认识到反式mitted。

89. 发明公开

EP3126243A1 SYSTEM AND METHOD FOR IMPROVED DRIVE SYSTEM DIAGNOSTICS 有权
标题翻译：系统VERFAHRENFÜRVERBESSERTE ANTRIEBSSYSTEMDIAGNOSE
公开(公告)号：EP3126243A1
公开(公告)日：2017-02-08
申请号：EP15772472.5
申请日：2015-04-02
申请人： Sikorsky Aircraft Corporation
发明人： SHELDON, Jeremy , KASPER, David , DAVIS, Mark, W.
IPC分类号： B64D45/00 , G01M17/00
CPC分类号： G07C5/00 , B64D45/00 , B64D2045/0085 , G05B23/0221
摘要： A method of drive system diagnostics of an aircraft includes capturing high load drivetrain component vibration data at select steady-state and/or high-load transient operating conditions of the aircraft and processing the captured vibration data to improve reliability and/or accuracy of the captured vibration data. The processed vibration data is utilized to provide a health assessment of the drivetrain components and achieve earlier detection of incipient faults. A health monitoring system for drivetrain components of an aircraft includes a plurality of vibration sensors positioned at drivetrain components of an aircraft to capture drivetrain component vibration data at transient operating conditions of the aircraft. One or more processing modules process the captured vibration data to improve reliability and/or accuracy of the captured data, and a fault reasoning module calculates a health indicator of the drivetrain components.
摘要翻译：一种飞行器的驱动系统诊断方法包括在飞行器的选择的稳态和/或高负载瞬态操作条件下捕获高负载传动系分量振动数据，并处理所捕获的振动数据，以提高捕获振动的可靠性和/或精确度数据。经处理的振动数据用于提供传动系组件的健康评估，并能早期检测初期故障。一种用于飞行器的传动系部件的健康监测系统包括多个位于飞行器的传动系部件上的振动传感器，用于在飞行器的瞬时操作条件下捕获传动系分量振动数据。一个或多个处理模块处理所捕获的振动数据以提高所捕获数据的可靠性和/或准确性，并且故障推理模块计算传动系统部件的健康指示器。

90. 发明公开

EP3126231A1 ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT 有权
标题翻译： HÖHENRUDERLASTREDUZIERUNGSSTEUERUNGFÜREINDREHFLÜGELFLUGZEUG
公开(公告)号：EP3126231A1
公开(公告)日：2017-02-08
申请号：EP14888084.2
申请日：2014-04-02
申请人： Sikorsky Aircraft Corporation
发明人： ELLER, Erez , GREENFIELD, Aaron L. , WULFF, Ole , WHITE, Matthew A. , LUSZCZ, Matthew T.
IPC分类号： B64C27/00
CPC分类号： B64C13/503 , B64C13/18 , B64C27/08 , B64C27/10 , B64C27/57 , B64C27/82 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281 , Y02T50/44
摘要： One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
摘要翻译：一个方面是用于包括主转子系统和电梯控制系统的旋翼飞机的飞行控制系统。飞行控制系统的飞行控制计算机包括配置成执行控制逻辑的处理电路。控制逻辑包括基于俯仰速率指令产生主转子前馈命令的逆电厂模型，以及负载减轻控制滤波器，其被配置为减小主转子系统上的负载并产生电梯控制系统的电梯命令。变换后的电梯指令滤波器基于电梯命令产生主转子音调调整指令，主转子指令发生器基于主转子前馈指令和主转子间距产生主转子系统的增大主转子前馈指令调整指令。

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