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公开(公告)号：US10380277B2
公开(公告)日：2019-08-13
申请号：US15122123
申请日：2015-03-02
摘要： A system and method for an application of a virtual load monitoring of an aircraft to determine a component retirement time for at least one component of the aircraft is provided. The system and method includes estimating component loads from aircraft state parameters; calculating load statistics from the component loads; calculating a reliability factor; generating a component design load spectrum by applying the reliability factor to the load statistics; and calculating the component retirement time for the at least one component of the aircraft by utilizing the component design load spectrum.
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2.发明授权公开(公告)号：US10337935B2
公开(公告)日：2019-07-02
申请号：US15835814
申请日：2017-12-08
发明人： Derek Geiger , Marcus D. Cappelli , Jonathan K. Garhart , Avinash Sarlashkar , Andrew Brookhart , Mark W. Davis
IPC分类号： G01L1/24 , G01M5/00 , H04B10/071 , G01M11/08 , G02B6/02 , G02B6/44 , B64D45/00 , G01N21/84 , G07C5/08
摘要： A fiber-optic sensor system includes a structure having a fiber-optic cable operatively connected thereto. The system includes a network controller with an interrogator operatively connected to the fiber-optic cable to receive optical energy indicative of a characteristic of the structure therefrom and convert optical energy to electrical energy and electrical energy to optical energy for data communication. A sensor and/or a data source are operatively connected to the fiber-optic cable through the network controller to transmit data through the fiber-optic cable and receive data therefrom.
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公开(公告)号：US20170336430A1
公开(公告)日：2017-11-23
申请号：US15534887
申请日：2015-10-19
发明人： Christopher L. Winslow , Biqing Wu , Mark W. Davis
CPC分类号： G01P3/4807 , G01H1/006 , G01P3/48 , G01P15/00
摘要： 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.
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公开(公告)号：US20170089805A1
公开(公告)日：2017-03-30
申请号：US15316017
申请日：2015-03-31
发明人： Jeremy Sheldon , Matthew James Watson , David Kasper , Avinash Sarlashkar , Jeffrey Steele , Mark W. Davis
CPC分类号： G01M13/028 , G01M13/02 , G01M17/00
摘要： 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.
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公开(公告)号：US10444254B2
公开(公告)日：2019-10-15
申请号：US15534887
申请日：2015-10-19
发明人： Christopher L. Winslow , Biqing Wu , Mark W. Davis
摘要： 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.
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公开(公告)号：US20180275044A1
公开(公告)日：2018-09-27
申请号：US15762029
申请日：2016-09-20
CPC分类号： G01N19/00 , G01H1/003 , G01M5/0066 , G01M13/028 , G01N3/32 , G01N19/08 , G01N29/043 , G01N29/14 , G01N29/36 , G01N29/42 , G01N29/4472 , G01N2291/0258 , G01N2291/106 , G01N2291/2694 , G06N20/00
摘要： A system and method are provided to perform loads-based structural health monitoring (LBSHM) of a dynamical system. The method includes receiving, by at least one computer, sensing data responsive to sensing at least one of a parametrical state and a response of the dynamical system, and determining a Koopman mode and a Koopman eigenvalue. The Koopman mode represents a correlation between the sensor data output by the plurality of sensors. The Koopman eigenvalue represents a frequency component associated with the sensor data and growth or decay of energy associated with the sensor data. The method further includes generating, by the at least one computer, an estimation model to determine a linear estimation based on the Koopman mode and the Koopman eigenvalue that estimates a load response of the dynamical system based on growth or decay of energy associated with the sensor data.
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公开(公告)号：US20170011560A1
公开(公告)日：2017-01-12
申请号：US15301152
申请日：2015-04-02
发明人： Jeremy Sheldon , David Kasper , Mark W. Davis
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 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定的稳态和/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。
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公开(公告)号：US10458863B2
公开(公告)日：2019-10-29
申请号：US13861784
申请日：2013-04-12
摘要： Virtual sensors can be used to monitor the loads on the system in determining damage accumulation, remaining useful life or retirement time of the components. A virtual sensor is a mathematical construct to infer a desired system measurement (e.g. a structural load) from readily available system state parameters (e.g. speed, weight, load factors, control settings, etc.). The accuracy of the virtual sensor depends upon the mapping between the desired measurement and the state parameters. A hybrid load monitoring system and method includes one or more direct or physical sensor measurements in addition to the plurality of virtual sensors. Signals from the physical sensors are included as an input (as opposed to an output) to the mapping between system state parameters and the various target sensor feature amplitudes.
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公开(公告)号：US10388087B2
公开(公告)日：2019-08-20
申请号：US15301623
申请日：2015-04-02
发明人： Isaac Bandy , James P. Cycon , James N. Rozak , Mark W. Davis , Gregory J. Kacprzynski , Nicholos A. Mackos
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.
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公开(公告)号：US10364050B2
公开(公告)日：2019-07-30
申请号：US15300655
申请日：2015-04-01
摘要： 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.
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