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公开(公告)号：US20190080524A1
公开(公告)日：2019-03-14
申请号：US15879207
申请日：2018-01-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker
Abstract: One embodiment is a system including a component for installation on a vehicle comprising a central maintenance computer (“CMC”); a configuration/maintenance module (“CMM”) associated with the component and including memory for storing component information, a sensor for detecting a condition and generating data indicative thereof; a microprocessor for processing the sensor data and updating the component information with the processing results; and a communications interface between the CMM and the CMC. The system further includes a remaining useful life (“RUL”) module associated with the component that periodically updates an RUL, the RUL module periodically updating an RUL value for the component and communicating the updated RUL value to the CMM for storage in the memory. The CMC communicates with the CMM to update the component information included in the memory based on information input to the CMC by a user or changes in a condition of the vehicle.
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公开(公告)号：US20160343044A1
公开(公告)日：2016-11-24
申请号：US14715773
申请日：2015-05-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Brian Messing
CPC classification number: G06Q30/0282 , G06Q10/20
Abstract: According to one example embodiment, an aircraft supplier feedback system includes an assessment engine and a transmission unit. The transmission unit is configured to transmit a comparison of a first-supplier characterization with an overall characterization to the first supplier and to transmit a comparison of a second-supplier characterization with the overall characterization to the second supplier. The characterizations are determined by the assessment engine based on feedback information associated with how a plurality of aircraft maintainers performed one or more aircraft maintenance actions.
Abstract translation: 根据一个示例性实施例，飞行器供应商反馈系统包括评估引擎和传输单元。 传输单元被配置为将第一供应商表征与整体表征的比较传送给第一供应商，并将第二供应商表征与整体表征的比较传送给第二供应商。 基于与多个飞机维护者如何执行一个或多个飞行器维护动作相关联的反馈信息，评估引擎确定特性。
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公开(公告)号：US20210272384A1
公开(公告)日：2021-09-02
申请号：US17321072
申请日：2021-05-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker
Abstract: One embodiment is a system including a component for installation on a vehicle comprising a central maintenance computer (“CMC”); a configuration/maintenance module (“CMM”) associated with the component and including memory for storing component information, a sensor for detecting a condition and generating data indicative thereof; a microprocessor for processing the sensor data and updating the component information with the processing results; and a communications interface between the CMM and the CMC. The system further includes a remaining useful life (“RUL”) module associated with the component that periodically updates an RUL, the RUL module periodically updating an RUL value for the component and communicating the updated RUL value to the CMM for storage in the memory. The CMC communicates with the CMM to update the component information included in the memory based on information input to the CMC by a user or changes in a condition of the vehicle.
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公开(公告)号：US09796479B2
公开(公告)日：2017-10-24
申请号：US14622403
申请日：2015-02-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Kevin Conrad , Chris Thompson , Brandon Johnson
IPC: B64D43/02 , B64D45/00 , G01M17/007 , B64F5/60
CPC classification number: B64D43/02 , B64D45/00 , B64D2045/0085 , B64F5/60 , G01M17/007
Abstract: An aircraft monitoring system includes multiple wireless aircraft sensors and multiple meta sensors mounted on-board an aircraft. Each wireless aircraft sensor is configured to sense an aircraft parameter. Each meta sensor is associated with an aircraft sensor and is configured to determine a location or orientation on the aircraft of the aircraft sensor. A data acquisition system mounted on-board the aircraft and connected to the multiple aircraft sensors and the multiple meta sensors can perform aircraft monitoring operations based on the sensed aircraft parameters and on a location or orientation of the aircraft sensors.
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公开(公告)号：US20160342956A1
公开(公告)日：2016-11-24
申请号：US14715783
申请日：2015-05-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Brian Mesing
CPC classification number: G06Q10/20 , B64D45/00 , B64D2045/0085 , B64F5/60 , G07C5/0841
Abstract: According to one example embodiment, an aircraft health feedback system includes an assessment engine and at least one receiver unit. The assessment engine is configured to identify, if the health data and the feedback data both indicate potential changes in health status of an aircraft part within the category of aircraft parts, a time lapse between when the health data indicates the potential change in health status of the aircraft part occurred and when the feedback information indicates that the potential change in health status was identified by at least one of the plurality of aircraft maintainers and to determine, if the health data and the feedback data both indicate potential changes in health status of an aircraft part within the category of aircraft parts, an error in at least one of the health data and the feedback information based on the time lapse.
Abstract translation: 根据一个示例实施例，飞行器健康反馈系统包括评估引擎和至少一个接收器单元。 评估引擎被配置为识别健康数据和反馈数据是否表示飞机部件类别内的飞机部件的健康状况的潜在变化，在健康数据表示健康状况的潜在变化之间的时间间隔 所述飞机部分发生，并且当所述反馈信息指示所述多个飞行器维护者中的至少一个识别出所述健康状态的潜在变化时，并且确定所述健康数据和所述反馈数据是否都表示潜在的健康状况变化 航空器部件类别中的飞机部件，基于时间流逝的至少一个健康数据和反馈信息中的错误。
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Patent Agency Ranking
公开(公告)号：US20160236794A1
公开(公告)日：2016-08-18
申请号：US14622403
申请日：2015-02-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Kevin Conrad , Chris Thompson , Brandon Johnson
IPC: B64D43/02 , B64D45/00 , G01M17/007
CPC classification number: B64D43/02 , B64D45/00 , B64D2045/0085 , B64F5/60 , G01M17/007
Abstract: An aircraft monitoring system includes multiple wireless aircraft sensors and multiple meta sensors mounted on-board an aircraft. Each wireless aircraft sensor is configured to sense an aircraft parameter. Each meta sensor is associated with an aircraft sensor and is configured to determine a location or orientation on the aircraft of the aircraft sensor. A data acquisition system mounted on-board the aircraft and connected to the multiple aircraft sensors and the multiple meta sensors can perform aircraft monitoring operations based on the sensed aircraft parameters and on a location or orientation of the aircraft sensors.
Abstract translation: 飞机监控系统包括安装在飞机上的多个无线飞行器传感器和多个元传感器。 每个无线飞行器传感器被配置成感测飞行器参数。 每个元传感器与飞行器传感器相关联并被配置成确定飞行器传感器的飞行器上的位置或取向。 安装在飞机上并连接到多个飞行器传感器和多个元传感器的数据采集系统可以基于所感测的飞行器参数以及飞行器传感器的位置或取向来执行飞行器监视操作。
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公开(公告)号：US09389071B2
公开(公告)日：2016-07-12
申请号：US14062387
申请日：2013-10-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Paul Madej
CPC classification number: G01B7/06 , G01B15/02 , G06K7/0008 , G06K19/0723 , G06K19/07749 , G07C9/00111 , H04B17/15 , H04B17/318
Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.
Abstract translation: 在一些方面，无线系统被配置为估计飞机表面上的材料层的厚度。 无线系统包括位于材料层下方的标签装置。 标签装置能够响应于电磁信号发送电磁信号。 在一些方面，收发器设备被配置为估计飞行器表面上的材料层的厚度。 收发器可以配置为使用电磁信号与标签进行通信。 收发器可以包括配置成测量信号强度并将信号强度与材料层的厚度相关联的一个或多个处理器。
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公开(公告)号：US20150370030A1
公开(公告)日：2015-12-24
申请号：US14310172
申请日：2014-06-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Drew Sutton , Brian Tucker , Troy Schank
CPC classification number: G01M11/086 , B64C27/007 , B64C27/33 , B64D2045/0085 , G01D5/3537 , G01D5/35374 , G02B6/00 , G02B2006/12138 , Y10T156/1002
Abstract: Some examples of techniques to cost-effectively embed fiber optic cables in laminate structures and to terminate the fiber optic cables on the surface of the laminate for robust and easily-repairable connections can be implemented in rotorcraft composites. To position a cable in the rotorcraft composite, a length of a fiber optic cable is embedded between layers of a composite rotorcraft material. The length of the fiber optic cable is oriented in a substantially S-shape between the layers. An end of the length of the substantially S-shaped fiber optic cable is extended to an edge of the composite rotorcraft material. The end of the length of the substantially S-shaped fiber optic cable is terminated at the edge of the composite rotorcraft material in either a storage area or easily machinable embedded connection.
Abstract translation: 将成本有效地将光纤电缆嵌入层压结构中的技术的一些实例并且终止层压板表面上的光纤电缆用于坚固且容易修理的连接可以在旋翼航空器复合材料中实现。 为了将电缆定位在旋翼航空器复合材料中，光纤电缆的长度被嵌入在复合旋翼航空器材料的层之间。 光纤电缆的长度在层之间取向为大致S形。 基本上S形的光纤电缆的长度的一端延伸到复合旋翼航空器材料的边缘。 基本上S形的光纤电缆的长度的端部终止于复合旋翼航空器材料在存储区域或易于加工的嵌入式连接中的边缘。
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公开(公告)号：US20150007666A1
公开(公告)日：2015-01-08
申请号：US14322312
申请日：2014-07-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Brian Tucker , Tom Wood , Robert Wardlaw , Bang Nguyen , Allen Altman
CPC classification number: G06F17/5095 , B64F5/60 , G01L5/00 , G05B19/4065 , G05B23/024 , G05B23/0254 , G05B23/0281 , G05B23/0283 , G05B2219/34477 , G05B2219/37253 , G07C5/085
Abstract: A method of monitoring usage of a component of an aircraft can include: monitoring a usage of the component by using a torque measurement system to calculate torque events in a time period; categorizing the usage of the component by assigning a usage value based upon whether the number of torque events in the period of time is above or below a threshold; and determining a life used of the component.
Abstract translation: 一种监视飞行器部件的使用的方法可以包括：通过使用扭矩测量系统来监视部件的使用以在一段时间内计算扭矩事件; 通过基于所述时间段中的扭矩事件的数量是否高于或低于阈值来分配使用值来对所述组件的使用进行分类; 并确定组件的使用寿命。
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公开(公告)号：US10442544B2
公开(公告)日：2019-10-15
申请号：US15586136
申请日：2017-05-03
Inventor： Douglas Boyd , Brian Tucker
Abstract: A multi-engine power system is described that includes at least a first engine and a second engine configured to jointly provided mechanical power to the multi-engine power system. The multi-engine power system further includes a controller configured to estimate a deterioration factor of the first engine. The controller is further configured to adjust, based on the deterioration factor of the first engine, a first amount of mechanical power being provided by the first engine to increase a service time of the first engine, and adjust, based on the first amount of mechanical power being provided by the first engine, a second amount of mechanical power being provided by the second engine to compensate for the adjustment to the first amount of mechanical power.
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