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

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： SHELDON, Jeremy ,  KASPER, David ,  ARGENNA, Garrett

IPC: G01D3/08 ,  G05B23/02

CPC classification number: G06F17/5009 ,  B64D45/00 ,  B64D2045/0085 ,  G05B23/0283 ,  G06Q10/20 ,  G07C5/0808

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2016191243A1

公开(公告)日：2016-12-01

申请号：PCT/US2016/033425

申请日：2016-05-20

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： SHELDON, Jeremy ,  MINNELLA, Christopher, M.

IPC: G01R31/28 ,  G01L25/00 ,  G01R31/27 ,  G01R31/3187 ,  G01R31/36

CPC classification number: G01R31/2829 ,  F16C19/527 ,  G01D3/08 ,  G01R31/008 ,  G01R31/27 ,  G01R31/3187 ,  G01R31/36

Abstract: A method for assessing the condition of a sensor includes applying a diagnostic signal to the sensor using a controller and receiving a dynamic output response. The dynamic output response includes a voltage transient and return to a baseline sensor output voltage. The dynamic output response is thereafter compared to a reference output response, and condition of the sensor is indicated as unreliable if the dynamic output response differs from the reference output response by a predetermined amount for a dynamic output response output parameter.

Abstract translation: 用于评估传感器状态的方法包括使用控制器将诊断信号应用于传感器并接收动态输出响应。 动态输出响应包括电压瞬变并返回到基线传感器输出电压。 此后，动态输出响应与参考输出响应进行比较，如果动态输出响应与参考输出响应不同，则将传感器的条件指示为不可靠，该动态输出响应对于动态输出响应输出参数为预定量。

公开(公告)号：WO2016178737A1

公开(公告)日：2016-11-10

申请号：PCT/US2016/020639

申请日：2016-03-03

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： LEE, Hyungdae ,  PALMER, Carl ,  KOELLE, Joshua Tyler ,  SHELDON, Jeremy

IPC: G01L25/00

CPC classification number: G01L25/00

Abstract: A system for strain gage calibration includes a data acquisition system operable to receive sensor inputs from a force sensor as a force input and a strain gage as a strain output. The strain gage detects a strain measurement of a structure under test in response to an excitation force applied by an excitation device, and the force sensor detects the excitation force. The system also includes a data processing system operable to perform calibration feature extraction of a plurality of calibration features from time and frequency domain responses of the force input and the strain output, and to determine a calibration factor of the strain gage based on a correlation of the calibration features to reference calibration features. The force input and the strain output are preprocessed before the calibration feature extraction to filter noise, remove outlying data, and temporally align the force input and the strain output.

Abstract translation: 用于应变计校准的系统包括数据采集系统，其可操作以从力传感器接收传感器输入作为力输入，应变计作为应变输出。 应变计响应于由激励装置施加的激励力来检测被测结构的应变测量，并且力传感器检测激励力。 该系统还包括可操作以从力输入和应变输出的时域和频域响应执行多个校准特征的校准特征提取的数据处理系统，并且基于相关性来确定应变计的校准因子 校准功能参考校准功能。 力输入和应变输出在校准特征提取之前进行预处理，以滤除噪声，去除外围数据，并在时间上对准力输入和应变输出。

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。

公开(公告)号：WO2015153845A1

公开(公告)日：2015-10-08

申请号：PCT/US2015/024013

申请日：2015-04-02

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： SHELDON, Jeremy ,  KASPER, David ,  DAVIS, Mark, W.

IPC: B64D45/00 ,  G01M17/00

CPC classification number: G07C5/00 ,  B64D45/00 ,  B64D2045/0085 ,  G05B23/0221

Abstract: 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.

Abstract translation: 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荷传动系分量振动数据，并处理所捕获的振动数据，以提高所捕获的振动数据的可靠性和/或准确性 振动数据。 经处理的振动数据用于提供传动系组件的健康评估，并实现早期检测初期故障。 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分量的健康指标。