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1.发明申请ROTORCRAFT STRUCTURAL FAULT-DETECTION AND ISOLATION USING VIRTUAL MONITORING OF LOADS 审中-公开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
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： ISOM, Joshua D. , DAVIS, Mark W. , CYCON, James Peter
IPC: G06F19/00
CPC classification number: G07C5/0825 , B64C27/32 , B64D2045/0085 , F02C3/10 , G01H1/006
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：WO2016099645A1
公开(公告)日：2016-06-23
申请号：PCT/US2015/056245
申请日：2015-10-19
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： WINSLOW, Christopher L. , WU, Biqing , DAVIS, Mark W.
IPC: G01H1/00
CPC classification number: G01P3/4807 , G01H1/006 , G01P3/48 , G01P15/00
Abstract: A system and method for receiving a plurality of first inputs from a transducer, where the plurality of first inputs correspond to vibrations of a rotational machine, and filtering the plurality of first inputs to derive a frequency of interest. The system and method then generates a sinusoidal signal at the frequency of interest and a pulse train of one or multiple pulses per revolution at the frequency of interest from the sinusoidal signal. The system and method further identifies a first pulse at a zero crossing within the pulse train and counts zero crossings to define blocks of data for use in time synchronous averaging calculations.
Abstract translation: 一种用于从换能器接收多个第一输入的系统和方法，其中所述多个第一输入对应于旋转机器的振动，并且对所述多个第一输入进行滤波以导出感兴趣的频率。 然后，系统和方法在感兴趣的频率处产生正弦信号，并且在正弦信号的感兴趣频率处产生每转一个或多个脉冲的脉冲串。 该系统和方法进一步识别在脉冲序列内零交叉处的第一脉冲，并对零交叉进行计数以定义在时间同步平均计算中使用的数据块。
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3.发明申请
公开(公告)号：WO2019054997A1
公开(公告)日：2019-03-21
申请号：PCT/US2017/051315
申请日：2017-09-13
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： WULFF, Ole , GEIGER, Derek H. , DAVIS, Mark W. , BROOKHART, Andrew M. , THORNBERG, Christopher A. , KUBIK, Stephen T.
IPC: B64D45/00 , G01M17/007 , G06F17/00 , H04N5/33
Abstract: A computer-implemented method and system for controlling an aircraft based on detecting and mitigating fatiguing conditions and aircraft damage conditions is disclosed. According to one example, a computer-implemented method includes detecting, by a processing system, a health condition of a component of the aircraft. The method further includes determining, by the processing system, whether the health condition is one of a fatigue condition or a damage condition. The method further includes implementing, by the processing system, a first action based at least in part on determining that the health condition is a fatigue condition to mitigate the fatigue condition. The method further includes implementing, by the processing system, a second action based at least in part on determining that the health condition is a damage condition to mitigate the damage condition.
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公开(公告)号：WO2015195184A2
公开(公告)日：2015-12-23
申请号：PCT/US2015/023811
申请日：2015-04-01
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： BROOKHART, Andrew , BATES, Preston R. , DAVIS, Mark W.
CPC classification number: B64F5/60 , B64D2045/0085 , G06Q10/08 , G07C5/0808
Abstract: A method of health monitoring and assessment of an aircraft structure includes collecting data from a plurality of sensors located at one or more components of the aircraft. The sensors assess a physical condition of the components and are arrayed in one or more aircraft zones. The data is communicated to a health assessment module, which calculates one or more component structural condition indicators of each component. The component structural condition indicators are compiled and one or more component structural health indicators are calculated. The component structural health indicators are compiled by aircraft zone and a zone structural health indicator is calculated based on the component structural health indicators of components residing in the particular aircraft zone. An aircraft level health indicator is calculated based on the zone structural health indicators and one or more maintenance actions are recommended based on the structural condition and health indicators.
Abstract translation: 飞行器结构的健康监测和评估的方法包括从位于飞行器的一个或多个部件上的多个传感器收集数据。 传感器评估组件的物理状况并排列在一个或多个飞机区域中。 将数据传送到健康评估模块，该模块计算每个组件的一个或多个组件结构状态指示器。 编制组成结构状况指标，并计算一个或多个组成部分结构健康指标。 部分结构健康指标由飞机区编制，区域结构健康指标是根据驻留在特定飞机区内的部件的部件结构健康指标计算的。 基于区域结构健康指标计算飞机级健康指标，并根据结构状况和健康指标推荐一个或多个维护措施。
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公开(公告)号：WO2011163316A2
公开(公告)日：2011-12-29
申请号：PCT/US2011/041374
申请日：2011-06-22
Applicant: SIKORSKY AIRCRAFT CORPORATION , ISOM, Joshua D. , DAVIS, Mark W. , WELSH, William A. , MORRIS, Brian Edward , CYCON, James Peter
Inventor： ISOM, Joshua D. , DAVIS, Mark W. , WELSH, William A. , MORRIS, Brian Edward , CYCON, James Peter
CPC classification number: B64D45/00 , B64D2045/0085 , B64F5/60 , G05B23/0243
Abstract: A system for monitoring for pushrod faults in an aircraft includes a pushrod; a sensor (36) mounted on the pushrod (34), the sensor (36) wirelessly transmitting measured pushrod load data; a receiver (44) receiving the measured pushrod load data; a model (42) receiving flight data and generating a modeled pushrod load profile; and a fault detector (46) comparing measured pushrod load data to the modeled pushrod load profile to detect a pushrod fault.
Abstract translation: 用于监视飞机中的推杆故障的系统包括推杆; 安装在推杆（34）上的传感器（36），所述传感器（36）无线地传送测量的推送负载数据; 接收器（44），接收测量的推送负载数据; 接收飞行数据并生成建模的推送负载曲线的模型（42）; 以及故障检测器（46）将测量的推送负载数据与建模的推送负载分布进行比较以检测推杆故障。
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公开(公告)号：WO2005015332A2
公开(公告)日：2005-02-17
申请号：PCT/US2004/025733
申请日：2004-08-09
Applicant: SIKORSKY AIRCRAFT CORPORATION , KHIBNIK, Alexander , ATALLA, Mauro Jorgre , FINN, Alan M. , DAVIS, Mark W. , MA, Jun , CYCON, James , HORBURY, Peter F. , BERNHARD, Andreas
Inventor： KHIBNIK, Alexander , ATALLA, Mauro Jorgre , FINN, Alan M. , DAVIS, Mark W. , MA, Jun , CYCON, James , HORBURY, Peter F. , BERNHARD, Andreas
IPC: G05B23/02
CPC classification number: G05B23/0221 , G05B13/04 , G05B17/02 , G05B19/4065 , G05B2219/37249
Abstract: A method and system estimates a desired output signal waveform based on measured state parameters. A model training step generates a model by empirically obtaining measured signal waveforms corresponding to measured state parameters. Features, such as mode shapes and mode amplitudes, are extracted from the measured signals and stored in an estimation model along with coefficients of the model that correlate measured state parameters with the mode amplitudes. During part operation, the state parameters measured during operation are entered into the estimation model to obtain estimated features in a estimated signal waveform. The estimated features are then used to synthesize the estimated signal reflecting the actual operation of the operating part. The estimation model therefore allows estimation of an entire signal waveform from the state parameters.
Abstract translation: 方法和系统基于测量的状态参数来估计期望的输出信号波形。 模型训练步骤通过经验获得对应于测量状态参数的测量信号波形来生成模型。 从测量信号中提取特征，例如模式形状和模式振幅，并将其与模型的系数一起存储在估计模型中，并将测量的状态参数与模式幅度相关联。 在部分操作期间，将运行期间测量的状态参数输入到估计模型中以获得估计信号波形中的估计特征。 然后使用估计的特征来合成反映操作部件的实际操作的估计信号。 因此，估计模型允许从状态参数估计整个信号波形。
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公开(公告)号：WO2016106353A1
公开(公告)日：2016-06-30
申请号：PCT/US2015/067451
申请日：2015-12-22
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： MASTRIANNI, Michael G. , SADEGH, Payman , DAVIS, Mark W. , JUDGE, John H.
CPC classification number: G01L1/26 , B64C25/001 , B64D45/00 , B64D2045/008 , G01B5/30 , G01B11/16 , G01M11/083
Abstract: A measuring system and method that computes and analyzes sensor data fused with multiple mechanical and thermally induced strain measurements is provided. Further, the measuring system and method realizes physics-based relations between sensor readings due to mechanical and thermal sources by optimally de-coupling a total strain into its mechanical and thermal components. The measuring system and method also auto-tunes coefficients involved in the optimal de-coupling equations using sensor specification data and previous system test results for initialization.
Abstract translation: 提供了一种计算和分析与多个机械和热诱导应变测量融合的传感器数据的测量系统和方法。 此外，测量系统和方法通过将总应变最佳地解耦到其机械和热部件中，实现由于机械和热源的传感器读数之间的基于物理学的关系。 测量系统和方法还使用传感器规格数据和先前的初始化系统测试结果自动调整参与最优解耦方程的系数。
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8.发明申请SYSTEM AND METHOD FOR IMPROVED HEALTH MANAGEMENT AND MAINTENANCE DECISION SUPPORT 审中-公开改进健康管理和维护决策支持的系统和方法
公开(公告)号：WO2015199782A2
公开(公告)日：2015-12-30
申请号：PCT/US2015/024011
申请日：2015-04-02
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： BANDY, Isaac , CYCON, James P. , ROZAK, James N. , DAVIS, Mark W. , KACPRZYNSKI, Gregory J. , MACKOS, Nicholas A.
IPC: G06Q10/08
CPC classification number: G07C5/0808 , G06Q10/20 , G07C5/006 , G07C5/008 , G07C5/0816
Abstract: 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.
Abstract translation: 监控系统的健康管理的方法包括收集用于计算多个组件健康指示符的组件状态指示符数据。 使用组件条件指示器数据确定组件故障严重性和潜在故障模式。 潜在的故障模式按照可能性的顺序排列故障模式。 用于被监视设备的健康管理系统包括：故障严重性模块，用于从收集的组件状态指示符数据中导出多个组件健康指示符，所述多个组件健康指示符指示多个组件的故障严重性。 故障隔离模块利用组件状态指示器数据分别列出潜在的故障/故障模式的列表。 该系统还包括一个通信部分，多个组件健康指示器和排列的故障/故障模式列表被发送到通信部分以供认知人员进行审查和/或动作。
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公开(公告)号：WO2015187241A1
公开(公告)日：2015-12-10
申请号：PCT/US2015/023526
申请日：2015-03-31
Applicant: SIKORSKY AIRCRAFT CORPORATION
Inventor： SHELDON, Jeremy , WATSON, Matthew James , KASPER, David , SARLASHKAR, Avinash , STEELE, Jeffrey , DAVIS, Mark W.
IPC: G01M17/00
CPC classification number: G01M13/028 , G01M13/02 , G01M17/00
Abstract: Embodiments are directed to obtaining data based on samples of a vibration signal, processing, by at least one processor, the data to obtain a qualitative and quantitative assessment of a health of the one or more components based on an application of the data to at least one model, and outputting the assessment. Embodiments of the disclosure may be applied to one or more components of a drive shaft of an aircraft.
Abstract translation: 实施例旨在基于振动信号的采样来获得数据，由至少一个处理器处理数据，以便基于数据的应用至少获得对一个或多个组件的健康状况的定性和定量评估 一种模式，并输出评估。 本公开的实施例可以应用于飞行器的驱动轴的一个或多个部件。
