公开(公告)号：EP2653847B1

公开(公告)日：2017-09-13

申请号：EP13163431.3

申请日：2013-04-11

申请人： The Boeing Company

发明人： Miller, Mark E. ,  Davis, George V.

IPC分类号： G01M7/02 ,  G01G19/07 ,  G01M1/12 ,  B64F5/00

CPC分类号： B64F5/0045 ,  B64F5/60 ,  G01G19/07 ,  G01M1/125 ,  G01M7/02 ,  G01M7/027

公开(公告)号：EP3173893A1

公开(公告)日：2017-05-31

申请号：EP16200450.1

申请日：2016-11-24

申请人： The Boeing Company

发明人： BUMGARDNER, Mark, D. ,  SCHWEIGER, Jonathan, A. ,  RANDICH, Timothy, W.

IPC分类号： G05D23/19 ,  G01R19/25 ,  B64F5/10

CPC分类号： F28F27/00 ,  B64F5/0009 ,  B64F5/0045 ,  F28C3/005 ,  F28D2021/0021 ,  G01K3/14 ,  G05D23/1934 ,  H04W4/80

摘要： Examples disclosed herein relate to methods and apparatus for controlling the temperature of large scale structures during manufacturing operations. A structure or surface when measured by Computer Aided Measuring Systems (CAMS) preferably remains a predetermined constant temperature with minimum variance. The manufacturing system includes a first temperature sensor, a second temperature sensor, a plurality of temperature regulation devices, and a processor, all in wireless communication. During performance of a CAMS process on a large scale structure or surface, a recorded temperature value of the structure or surface is communicated. A determination is made based on the recorded temperature value to operate the plurality of temperature regulation devices to control the temperature of targeted areas of the structure or surface. The temperature regulation devices are monitored and controlled such that the structure or surface is stabilized and distortion is prevented during the CAMS process.

摘要翻译： 本文公开的示例涉及用于在制造操作期间控制大型结构的温度的方法和设备。 当通过计算机辅助测量系统（CAMS）测量时，结构或表面优选保持具有最小偏差的预定恒定温度。 制造系统包括全部无线通信的第一温度传感器，第二温度传感器，多个温度调节装置和处理器。 在大规模结构或表面上执行CAMS过程期间，传达结构或表面的记录温度值。 基于记录的温度值进行确定以操作多个温度调节装置以控制结构或表面的目标区域的温度。 监视和控制温度调节装置，以便在CAMS过程期间结构或表面稳定并防止变形。

公开(公告)号：EP3108317A1

公开(公告)日：2016-12-28

申请号：EP15707458.4

申请日：2015-02-11

申请人： GE Aviation Systems LLC

发明人： PEREIRA, Frazer Leslie

IPC分类号： G05B23/02

CPC分类号： G07C5/0808 ,  B64F5/0045 ,  B64F5/60 ,  G01R31/008 ,  G05B23/0264 ,  G05B23/0283

摘要： A fault monitoring system for an aircraft includes a processor having a fault diagnosis algorithm, a memory connected to the processor, a plurality of sensors located at selected nodes in an electrical network of the aircraft and connected to the processor, and a data collection algorithm in one of the processor or the plurality of sensors. Each sensor is configured to continuously monitor voltage and current of the electrical network at its selected node and to transmit data representative of the monitored voltage and current to the processor. Upon the occurrence of a fault event, the data collection algorithm selects a subset of the data related to the fault event and at least one sensor transmits a selected subset of the data to one of the processor or the memory.

摘要翻译： 一种用于飞行器的故障监测系统包括具有故障诊断算法的处理器，连接到处理器的存储器，位于飞行器的电气网络中并连接到处理器的选定节点处的多个传感器，以及数据采集算法 处理器或多个传感器之一。 每个传感器被配置为连续地监视其所选节点处的电网络的电压和电流，并将表示所监视的电压和电流的数据传送到处理器。 在出现故障事件时，数据采集算法选择与故障事件有关的数据的子集，并且至少一个传感器将选定的数据子集发送到处理器或存储器之一。

公开(公告)号：EP3096123A1

公开(公告)日：2016-11-23

申请号：EP16170074.5

申请日：2016-05-18

申请人： Embraer S.A.

发明人： Da Silva, Paulo Anchieta ,  Dotta, Fernando ,  Rulli, Ricardo Pinheiro ,  Lazanha, Tomaz ,  Suzuki, Marcelo Rosa ,  De Moraes Da Costa, Laudier Jacques ,  Wallner, Cassio ,  Rogulski, Ricardo

IPC分类号： G01M5/00 ,  B60R16/023 ,  G07C5/00

CPC分类号： B64F5/0045 ,  B60R16/0234 ,  B64D45/00 ,  B64D2045/0085 ,  G01M5/0033 ,  G01M5/0066 ,  G01M17/007 ,  G07C5/006 ,  G07C5/008 ,  G07C5/0808

摘要： An integrated system for assessing the condition and management of a structural platform or a plurality of platforms includes a Structural Health Monitoring System (SHM), an Operational loads Monitoring System (OLM), a static, fatigue and damage tolerance analysis (FDTA) subsystem, a databank storing a maintenance plan, and a subsystem configured for damage and repair management (iSRM). The SHM may include a plurality of transducers, including a plurality of pairs of actuators and sensors; a generator device configured to excite at least one of said sensors to produce ultrasonic guided waves; and a signal processor device configured to receive the signals reflected from damage identification. The Operational loads Monitoring System (OLM) may comprise parametric models using flight parameter data. The static, fatigue and damage tolerance analysis (FDTA) subsystem may be configured to use parametric models using Finite element Models results and abacus. The databank storing a maintenance plan may comprise information relating to inspection periods and tasks of the structural platform or a plurality of platforms.

摘要翻译： 对于assesing结构平台的条件和管理的集成系统或平台的多元性包括结构健康状态监测系统（SHM）至操作载荷监控系统（OLM），静态，疲劳和损伤容限分析（FDTA）子系统， 一个数据库中存储的维护计划，并且被配置用于损伤和修复管理（ISRM）的子系统。 的SHM可以包括换能器，包括对致动器和传感器中的多个A多元性; 配置成激励所述传感器以产生超声导波中的至少一种的发电装置; 和配置为接收所述信号的信号处理器设备从损伤识别反射。 的操作载荷监控系统（OLM）可以使用飞行参数数据包括参数化模型。 静态，疲劳和损伤容限分析（FDTA）子系统可以被配置为使用利用有限元模型的结果和算盘参数模型。 该数据库中存储的维护计划可以包括信息与检验周期和结构平台或平台的多个任务。

公开(公告)号：EP2902325B1

公开(公告)日：2016-11-09

申请号：EP15153441.9

申请日：2015-02-02

申请人： AIRBUS OPERATIONS (S.A.S)

发明人： Poux, Thibaut ,  Buron, François ,  Mesguen, Maël

IPC分类号： B64D43/00 ,  G01C23/00

CPC分类号： B64F5/0045 ,  B60L2250/16 ,  B64D43/00 ,  B64D2045/0085

公开(公告)号：EP2562090A2

公开(公告)日：2013-02-27

申请号：EP12181532.8

申请日：2012-08-23

申请人： The Boeing Company

发明人： Pedigo, Samuel F ,  JOhnson, Brice A ,  Battles, Craig F ,  Kaiser, Donald L ,  Kaiser, Kimberly J ,  Blair, Richard N ,  Li, Winfeng ,  Cobb, James M ,  Smith, Matthew W

IPC分类号： B64F5/00 ,  G06Q10/00

CPC分类号： B64F5/0045 ,  B64F5/60 ,  G01B5/008 ,  G06F17/40 ,  G06F19/00 ,  G06Q10/06 ,  G06Q50/04 ,  Y02P90/30

摘要： An anomaly detection and cataloging system is described that includes a handheld probe having a probe tip, a user interface, and a communications interface. The system further includes a system controller and a probe locating device. The probe is operable, via the user interface, for transmitting, via the communications interface, a user selected anomaly type to the system controller, the anomaly type being associated with a manufactured part or airplane on the ground (AOG). The probe locating device is operable to provide to the system controller a location associated with the probe tip, and the system is programmed to associate the user selected anomaly type with the location associated with the probe tip.

公开(公告)号：EP3196119A1

公开(公告)日：2017-07-26

申请号：EP17150619.9

申请日：2017-01-09

申请人： The Boeing Company

发明人： THOMAS, Jeffrey M ,  ALDERETE, David ,  COSTELLO, Richard

IPC分类号： B64C27/00 ,  B64C27/39 ,  B64C27/48

CPC分类号： B64C27/39 ,  B64C27/008 ,  B64C27/48 ,  B64C27/78 ,  B64F5/0045 ,  B64F5/60

摘要： A rotorcraft (10) including a rotor hub (26), a pitch housing (30) moveable relative to the rotor hub (26) about at least a feather axis (A2) and a flap axis (A1), the pitch housing (30) defining an internal volume (40), a bearing pin (60), the inboard end portion of the bearing pin (60) being fixedly connected to the rotor hub (26), wherein the bearing pin (60) defines the feather axis (A2), a spherical bearing (62) connected to the inboard end portion (32) of the pitch housing (30) and defining the flap axis (A1), wherein the bearing pin (60) extends through the spherical bearing (62), a rotor blade (28) connected to the outboard end portion (34) of the pitch housing (30), and a sensor assembly (50) positioned in the internal volume (40) and operatively connected to both the pitch housing (30) and the outboard end portion (78) of the bearing pin (60).

摘要翻译： 一种旋翼飞行器（10），其包括转子轮毂（26），可相对于转子轮毂（26）围绕至少羽轴轴线（A2）和翼片轴线（A1）移动的桨距壳体（30），桨距壳体 ）限定内部体积（40），轴承销（60），轴承销（60）的内侧端部固定地连接到转子轮毂（26），其中轴承销（60）限定了轴线 A2）;球面轴承（62），所述球面轴承连接到所述桨叶壳体（30）的所述内侧端部（32）并且限定所述翼片轴线（A1），其中所述轴承销（60）延伸穿过所述球面轴承（62） 连接到桨距壳体30的外侧端部34的转子叶片28以及定位在内部容积40中并且可操作地连接到桨距壳体30和30的传感器组件50。 轴承销（60）的外侧端部（78）。

公开(公告)号：EP2701025B1

公开(公告)日：2017-07-19

申请号：EP13158862.6

申请日：2013-03-12

申请人： Bell Helicopter Textron Inc.

发明人： Plowman, Larry A ,  Covington, Charles Eric ,  Tucker, Brian E

IPC分类号： G05B23/02 ,  B64D45/00 ,  B64F5/00

CPC分类号： B64F5/0045 ,  B64D45/00 ,  B64D2045/0085 ,  B64F5/60 ,  G05B23/0275 ,  G07C5/085

公开(公告)号：EP3043323A3

公开(公告)日：2016-08-03

申请号：EP16150742.1

申请日：2016-01-11

申请人： Hamilton Sundstrand Corporation

发明人： DeRoy, Robert M.

IPC分类号： G07C5/08

CPC分类号： B64F5/0045 ,  B64D13/08 ,  B64D2013/0603 ,  B64F5/60 ,  G07C5/085

摘要： In one example, a system 10 includes a component 20 of an air management system 16 of an aircraft and an active history memory module 12 attached to the component 20. The active history memory module 12 includes interface circuitry 28 configured to receive data corresponding to one or more operational parameters of the aircraft. The active history memory module 12 further includes computer-readable memory 30 operably connected to the interface circuitry 28 and configured to store the data corresponding to the one or more operational parameters.

公开(公告)号：EP3043323A2

公开(公告)日：2016-07-13

申请号：EP16150742.1

申请日：2016-01-11

申请人： Hamilton Sundstrand Corporation

发明人： DeRoy, Robert M.

IPC分类号： G07C5/08

CPC分类号： B64F5/0045 ,  B64D13/08 ,  B64D2013/0603 ,  B64F5/60 ,  G07C5/085

摘要： In one example, a system 10 includes a component 20 of an air management system 16 of an aircraft and an active history memory module 12 attached to the component 20. The active history memory module 12 includes interface circuitry 28 configured to receive data corresponding to one or more operational parameters of the aircraft. The active history memory module 12 further includes computer-readable memory 30 operably connected to the interface circuitry 28 and configured to store the data corresponding to the one or more operational parameters.

摘要翻译： 在一个示例中，系统10包括飞行器的空气管理系统16的组件20和附接到组件20的活动历史存储器模块12.活动历史存储器模块12包括接口电路28，接口电路28被配置为接收对应于一个 或更多的飞机操作参数。 主动历史存储器模块12进一步包括计算机可读存储器30，其可操作地连接到接口电路28并且被配置为存储对应于一个或多个操作参数的数据。