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    NON-CONTACT CONTROL ROD MONITOR (NCM)
    11.
    发明申请
    NON-CONTACT CONTROL ROD MONITOR (NCM) 审中-公开
    非接触式控制监视器（NCM）

    公开(公告)号：WO2015175065A3

    公开(公告)日：2016-01-07

    申请号：PCT/US2015016486

    申请日：2015-02-19

    Applicant: EIT LLC

    Inventor： MAY JOE ,  MURDOCH CHRISTOPHER ,  MCCONNELL MATTHEW

    IPC: G05G9/047 ,  B64C27/54 ,  G05D1/08

    CPC classification number: B64C13/04 ,  B64D2045/0065 ,  B64D2045/0085

    Abstract: A non-contact control rod monitor (NCM) includes non-contact sensors for monitoring the positions of the four control rods of a rotary wing aircraft. In an exemplary embodiment, target indicia are arranged on the control rods to assist in detection of their positions with optical sensors. The detected positions are transmitted to a processor which converts the data to position information for the collective, cyclic, and anti-torque pedal controls of the aircraft.

    Abstract translation: 非接触式控制杆监视器（NCM）包括用于监视旋翼飞机的四个控制杆的位置的非接触式传感器。 在示例性实施例中，目标标记被布置在控制杆上以帮助用光学传感器检测它们的位置。 检测到的位置被发送到处理器，该处理器将数据转换为飞行器的集体的，循环的和反转矩踏板控制的位置信息。

    SYSTEM AND METHOD FOR IMPROVED DRIVE SYSTEM DIAGNOSTICS
    12.
    发明申请
    SYSTEM AND METHOD FOR IMPROVED DRIVE SYSTEM DIAGNOSTICS 审中-公开
    用于改进驱动系统诊断的系统和方法

    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。

    SYSTEM AND METHOD FOR HEALTH MONITORING OF HYDRAULIC SYSTEMS
    13.
    发明申请
    SYSTEM AND METHOD FOR HEALTH MONITORING OF HYDRAULIC SYSTEMS 审中-公开
    液压系统健康监测系统与方法

    公开(公告)号：WO2015153731A1

    公开(公告)日：2015-10-08

    申请号：PCT/US2015/023830

    申请日：2015-04-01

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： SMITH, Matthew J. ,  KLODA, Jared ,  FRIEL, Jason ,  HETTLER, Eric

    IPC: G01M3/28

    CPC classification number: F15B19/005 ,  B64D2045/0085 ,  F15B20/005 ,  F15B2211/6303 ,  F15B2211/6306 ,  F15B2211/6343 ,  G01F23/00 ,  G01F25/0061 ,  G01M3/002 ,  G01M3/28 ,  G01M3/3245 ,  G05B23/0283

    Abstract: A method of health monitoring of a hydraulic system includes measuring a hydraulic fluid level at a first location in the hydraulic systems and measuring one or more of hydraulic fluid pressure and hydraulic fluid temperature at one or more second locations in the hydraulic system. A snapshot of data is identified that meets a mode detection criteria a model requires to estimate the hydraulic fluid level. An expected hydraulic fluid level is calculated based on the measurements of hydraulic fluid pressure and/or hydraulic fluid temperature, and the expected hydraulic fluid level is compared to the measured hydraulic fluid level, the difference an indicator of leakage in the hydraulic system.

    Abstract translation: 液压系统的健康监测方法包括测量液压系统中的第一位置处的液压液位，并测量液压系统中一个或多个第二位置处的液压流体压力和液压流体温度中的一个或多个。 识别数据的快照，其符合模型所需要的估计液压液位的模式检测标准。 基于液压流体压力和/或液压流体温度的测量来计算预期的液压液位，并且将预期的液压液位与所测量的液压液位进行比较，所述液压系统中泄漏指标的差异。

    SYSTEM AND METHOD FOR HEATLH MONITORING OF SERVO-HYDRAULIC ACTUATORS
    14.
    发明申请
    SYSTEM AND METHOD FOR HEATLH MONITORING OF SERVO-HYDRAULIC ACTUATORS 审中-公开
    用于伺服液压执行机构的热监测的系统和方法

    公开(公告)号：WO2015153727A2

    公开(公告)日：2015-10-08

    申请号：PCT/US2015/023819

    申请日：2015-04-01

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： SMITH, Matthew J. ,  KLODA, Jared ,  FRIEL, Jason ,  HETTLER, Eric

    IPC: G06F19/00

    CPC classification number: F15B19/005 ,  B64D2045/0085 ,  F15B20/005 ,  F15B2211/6303 ,  F15B2211/6306 ,  F15B2211/6343 ,  G01F23/00 ,  G01F25/0061 ,  G01M3/002 ,  G01M3/28 ,  G01M3/3245 ,  G05B23/0283

    Abstract: A method of health monitoring of a hydraulic actuator includes sensing a first hydraulic fluid pressure at a first chamber of a hydraulic cylinder, the first chamber defined by a piston disposed in the cylinder and a first cylinder wall. The method further includes sensing a second hydraulic fluid pressure at a second chamber of the hydraulic cylinder, the second chamber defined by the piston and a second cylinder wall opposite the first cylinder wall. The pressures are summed to derive a pressure sum leakage estimate. An actual piston position in the hydraulic cylinder is determined and compared to an intended piston position to determine a positional error of the piston. A command-response error leakage estimate is derived from the positional error. The pressure sum leakage estimate and the command-response error leakage estimate are fused to determine an internal hydraulic fluid leakage in the hydraulic cylinder.

    Abstract translation: 液压致动器的健康监测方法包括检测液压缸的第一腔室处的第一液压流体压力，第一腔室由设置在缸体中的活塞和第一缸体壁限定。 该方法进一步包括检测液压缸的第二腔室处的第二液压流体压力，第二腔室由活塞和与第一缸壁相对的第二缸壁限定。 将压力相加以得出压力总和泄漏估计值。 确定液压缸中的实际活塞位置并将其与预期的活塞位置进行比较以确定活塞的位置误差。 命令 - 响应误差泄漏估计来自位置误差。 压力总和泄漏估计和命令 - 响应误差泄漏估计被熔合以确定液压缸内的液压流体泄漏。

    ASSESSING INTEGRITY OF BONDED JOINTS
    15.
    发明申请
    ASSESSING INTEGRITY OF BONDED JOINTS 审中-公开
    评估焊接接头的完整性

    公开(公告)号：WO2015091390A1

    公开(公告)日：2015-06-25

    申请号：PCT/EP2014/077820

    申请日：2014-12-15

    Applicant: BAE SYSTEMS PLC

    Inventor： READ, Ian, James

    IPC: G01M5/00 ,  G01M11/08 ,  G02B6/36 ,  B64D45/00 ,  F03D7/00 ,  B29C65/82 ,  B29C65/48

    CPC classification number: G01M11/086 ,  B29C65/48 ,  B29C65/4835 ,  B29C65/50 ,  B29C66/1122 ,  B29C66/45 ,  B29C66/50 ,  B29C66/69 ,  B29C66/721 ,  B29C66/82 ,  B29L2011/0075 ,  B29L2031/085 ,  B29L2031/3076 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64C2001/0072 ,  B64D45/00 ,  B64D2045/0085 ,  G02B6/3644 ,  Y02P70/523

    Abstract: There is provided apparatus and a method for assessing the integrity of a bonded joint and a bonded joint assembly. The assembly has a bonded joint monitored for bond integrity and comprises first (1) and second (2) components each defining a bonding surface (3,4); the joint (5) is formed between the bonding surfaces (3,4) and the first component (1) defines a passage (15) therethrough from the bonding surface to an exterior of the component. The joint (5) includes an optical fibre (11) extending along the joint (5) between the bonding surfaces, through the passage (15) and emerging from the passage (15) to the exterior of the component. The method of constructing the assembly includes the steps of passing the optical fibre (11) through the passage (15) and adhering the optical fibre (11) to the bonding surface (3) of the first component (1), thus bringing the two bonding surfaces (3,4) together and forming the bond (5).

    Abstract translation: 提供了用于评估接合接头和接合接头组件的完整性的装置和方法。 所述组件具有粘结接头，用于粘合完整性，并包括每个限定粘合表面（3,4）的第一（1）和第二（2）部件。 接头（5）形成在接合表面（3,4）之间，并且第一部件（1）限定从接合表面到部件外部的通道（15）。 接头（5）包括通过通道（15）沿着接合部（5）延伸并且从通道（15）向部件外部延伸的光纤（11）。 构成组件的方法包括使光纤（11）穿过通道（15）并将光纤（11）粘附到第一部件（1）的接合表面（3）的步骤，从而使两个 接合表面（3,4）在一起并形成键（5）。

    FLAP ANGLE MEASUREMENT SYSTEM AND METHOD
    16.
    发明申请
    FLAP ANGLE MEASUREMENT SYSTEM AND METHOD 审中-公开
    襟翼角度测量系统及方法

    公开(公告)号：WO2015053671A1

    公开(公告)日：2015-04-16

    申请号：PCT/SE2013/051192

    申请日：2013-10-10

    Applicant: SAAB AB

    Inventor： BERGELIN, Magnus ,  ERLANDSSON, Kristian

    IPC: B64C27/32

    CPC classification number: G01D5/12 ,  B64C27/008 ,  B64C27/39 ,  B64D2045/0085 ,  G07C5/0808 ,  B64D1/18 ,  B64C39/024

    Abstract: The invention relates to a system for monitoring movements of the rotor blades attached by flapping hinges (7) to a central head (4) or hub of a helicopter. The invention is achieved by that at least one sensor (9) is arranged to continuously measure the vertical angular movement (α) of a rotor blade and/or the flapping hinge (7).The invention also includes a method for monitoring the same movements.

    Abstract translation: 本发明涉及一种用于监视通过将铰链（7）附接到直升机的中心头部（4）或毂的附接的转子叶片的运动的系统。 本发明通过以下方式实现：至少一个传感器（9）布置成连续地测量转子叶片和/或摇动铰链（7）的垂直角运动（α）。本发明还包括一种用于监测相同运动 。

    METHODS, SYSTEMS AND APPARATUS FOR AUTOMATED GENERATION OF A FLIGHT LOG AND A SQUAWK LIST FILE
    18.
    发明申请
    METHODS, SYSTEMS AND APPARATUS FOR AUTOMATED GENERATION OF A FLIGHT LOG AND A SQUAWK LIST FILE 审中-公开
    自动生成飞行日志和SQUAWK列表文件的方法，系统和设备

    公开(公告)号：WO2015013307A1

    公开(公告)日：2015-01-29

    申请号：PCT/US2014/047664

    申请日：2014-07-22

    Applicant: GULFSTREAM AEROSPACE CORPORATION ,  ODELL, Robert ,  GALLAGHER, Jim ,  CONZACHI, Keith ,  BRITT, Noelle ,  CLAFFY, Kevin ,  KEREKESH, William

    Inventor： ODELL, Robert ,  GALLAGHER, Jim ,  CONZACHI, Keith ,  BRITT, Noelle ,  CLAFFY, Kevin ,  KEREKESH, William

    IPC: G08G5/00

    CPC classification number: G07C5/008 ,  B64D45/00 ,  B64D2045/0085 ,  B64F5/60 ,  G07C5/085

    Abstract: The disclosed embodiments relate to methods, systems and apparatus for automated generation a flight log and a squawk list file. A computer records a preliminary flight log data file (PFLDF), and automatically generates a preliminary squawk list file (PSLF) that includes a plurality of squawk events recorded while an aircraft is in flight. A wireless communication device includes a processor configured to execute a software application, a display that displays a graphical user interface that presents each squawk event from the PSLF for review, and an input system configured to receive inputs including an input for each particular squawk event.

    Abstract translation: 所公开的实施例涉及用于自动生成飞行日志和啸叫列表文件的方法，系统和装置。 计算机记录初步飞行日志数据文件（PFLDF），并且自动生成包括在飞行中飞行中记录的多个突发事件的初步啸叫列表文件（PSLF）。 无线通信设备包括被配置为执行软件应用的处理器，显示图形用户界面的显示器，所述图形用户界面从PSLF呈现每个尖叫事件以进行审查;以及输入系统，被配置为接收包括用于每个特定尖叫事件的输入的输入。

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