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    TOTAL AIR TEMPERATURE SENSORS
    81.
    发明授权
    TOTAL AIR TEMPERATURE SENSORS 有权

    公开(公告)号：EP3101399B1

    公开(公告)日：2018-10-03

    申请号：EP16180210.3

    申请日：2014-10-15

    Applicant: Rosemount Aerospace Inc.

    Inventor： SCHWIE, Chester ,  CORNIEA, Kyle ,  JEWETT, Erik

    IPC: G01K13/02

    CPC classification number: B64F1/26 ,  G01K13/028

    Abstract: A total air temperature sensor includes a probe head (102), a strut (104), and a turbulence inducing surface (116). The probe head has an airflow inlet (106) and an airflow outlet (108). The strut defines a leading edge (110) and an opposed trailing edge (112) extending along a longitudinal axis (A), and connects between the probe head and an opposed probe mount (114). The turbulence inducing surface is defined in the strut aft the leading edge. The turbulence inducing surface is configured to trip a fluid boundary layer passing over the strut to transition from laminar to turbulent for moving flow separation toward the trailing edge to reduce acoustic noise emission from the total air temperature sensor.

    PROBE HEATER REMAINING USEFUL LIFE DETERMINATION
    82.
    发明公开
    PROBE HEATER REMAINING USEFUL LIFE DETERMINATION 审中-公开

    公开(公告)号：EP3379263A1

    公开(公告)日：2018-09-26

    申请号：EP18153830.7

    申请日：2018-01-29

    Applicant: Rosemount Aerospace Inc.

    Inventor： ESSAWY, Magdi ,  MCTIGHE, James ,  FOK, Ben

    IPC: G01P5/165 ,  G01P13/02 ,  G01K13/02 ,  G01K15/00 ,  G01R31/00 ,  H05B3/56

    Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system. The control circuit is configured to provide the operational voltage and monitor a circuit frequency based on an element capacitance between the resistive heating element and a metallic sheath of the heater over time. The control circuit is further configured to determine remaining useful life of the probe system based on the circuit frequency.

    ULTRA-WIDEBAND RADAR ALTIMETER
    83.
    发明公开
    ULTRA-WIDEBAND RADAR ALTIMETER 审中-公开

    公开(公告)号：EP3367123A1

    公开(公告)日：2018-08-29

    申请号：EP18157911.1

    申请日：2018-02-21

    Applicant: Rosemount Aerospace Inc.

    Inventor： PESIK, Joseph ,  ELL, Todd Anthony

    IPC: G01S13/88 ,  G01S13/02 ,  G01S13/10

    CPC classification number: G01S13/882 ,  G01S7/032 ,  G01S13/0209 ,  G01S13/10

    Abstract: A system can include an unmanned aerial vehicle (10) and an altimeter disposed on the unmanned aerial vehicle. The altimeter can include an ultra-wideband radar antenna (12) disposed orthogonally to a plane of straight and level flight of the unmanned aerial vehicle and having an omnidirectional azimuthal beam pattern orthogonal to the plane of straight and level flight of the unmanned aerial vehicle. The altimeter can be configured to determine an altitude of the unmanned aerial vehicle above a target surface based on time of flight of radar pulses between the ultra-wideband radar antenna and the target surface.

    CONTROLLED SAMPLING VOLUME OF CLOUDS FOR MEASURING CLOUD PARAMETERS
    85.
    发明公开
    CONTROLLED SAMPLING VOLUME OF CLOUDS FOR MEASURING CLOUD PARAMETERS 审中-公开

    公开(公告)号：EP3351967A3

    公开(公告)日：2018-08-08

    申请号：EP18152834.0

    申请日：2018-01-22

    Applicant: Rosemount Aerospace Inc.

    Inventor： RAY, Mark ,  ANDERSON, Kaare Josef

    IPC: G01S17/95 ,  G01S7/481 ,  B64D15/20 ,  G01N15/02

    CPC classification number: G01N15/0211 ,  B64D15/20 ,  G01N21/49 ,  G01N2015/0026 ,  G01S7/4811 ,  G01S7/4815 ,  G01S7/4818 ,  G01S17/95 ,  G01W1/00 ,  Y02A90/19

    Abstract: Apparatus and associated methods relate to determining a size and/or density of Super-cooled Large Droplets (SLDs) in a cloud atmosphere by comparing detected optical signals reflected from small and large sampling volumes of a cloud atmosphere. In some embodiments, an optical pulse is generated and divergently projected from a first optical fiber. A collimating lens (30) is aligned within the divergently projected optical pulse collimating a portion thereof. The collimated and uncollimated portions of the optical pulse are projected into the small and large sampling volumes of the cloud atmosphere, respectively. The ratio of the collimated to the uncollimated portions can be optically controlled. Signals corresponding to optical pulses having different collimated/uncollimated ratios are backscattered by the cloud atmosphere, detected and compared to one another. A processor is configured to calculate, based on scintillation spike differences between the optical pulses of different collimated/uncollimated ratios, a size and/or density of SLDs.

    AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS
    87.
    发明公开
    AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS 审中-公开
    使用飞机增量模式自动超冷却水滴尺寸差异

    公开(公告)号：EP3263460A1

    公开(公告)日：2018-01-03

    申请号：EP17178461.4

    申请日：2017-06-28

    Applicant: Rosemount Aerospace Inc.

    Inventor： LoPresto, Vincent R. ,  MATHEIS, Brian Daniel

    IPC: B64D15/20 ,  G08B19/02

    CPC classification number: B64D15/20 ,  B64D45/00 ,  B64D47/08 ,  G01N15/0227 ,  G08B19/02

    Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, whether an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A convex-shaped housing is mounted to an aircraft and exposed to an airstream. The convex-shaped housing has a testing region that is monitored for ice accretion by an ice detector. A boundary locator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets up to the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of an atmosphere containing super-cooled water droplets that equal or exceed the predetermined size.

    Abstract translation: 装置和相关方法涉及基于积冰的空间范围确定大气是否包含等于和/或超过预定尺寸的过冷水滴。 一个凸形的外壳安装在飞机上并暴露在气流中。 凸形外壳具有测试区域，该测试区域由冰检测器监测冰积聚。 边界定位器确定测试区域内要测试的特定位置。 如果大气包含达到预定尺寸的过冷水滴，则确定的特定位置对应于计算的边界，该边界将冰积累区域与无冰区域分开。 如果冰检测器在确定的特定位置检测到积冰，则生成警报。 警报可以有利地向飞行员通知包含等于或超过预定尺寸的过冷水滴的气氛。

    OPTICALLY POWERED TRANSDUCER MODULE
    88.
    发明公开
    OPTICALLY POWERED TRANSDUCER MODULE 审中-公开
    光电传感器模块

    公开(公告)号：EP3253068A1

    公开(公告)日：2017-12-06

    申请号：EP17162983.5

    申请日：2017-03-27

    Applicant: Rosemount Aerospace Inc.

    Inventor： DINH, Nghia T. ,  HUYNH, Cuong Tho ,  ISEBRAND, Scott D.

    IPC: H04Q9/00 ,  G08C23/06

    CPC classification number: H04B10/25 ,  G08C23/06 ,  H02J7/345 ,  H02J7/355 ,  H04Q9/00

    Abstract: A sensor assembly comprises a remote data concentrator (RDC) (14) and an optically powered transducer module (OPTM) (12). The RDC (14) transmits a first optical pulse including a parameter request signal along an optical fiber (16). The OPTM (12) is connected to the optical fiber (16), and comprises a photodiode (22), an energy storage device (30), a sensor (36), a processor (32), and a laser (24). The photodiode (22) receives the first optical pulse, and the energy storage device (30) is charged by the photodiode (22). The sensor (36), processor (32), and laser (24) are powered by discharging the energy storage device (30). The sensor (36) senses a parameter specified by the parameter request signal. The processor (32) generates a signal packet from the output of the first sensor (36). The laser transmits a second optical pulse including the signal packet along the optical fiber to the RDC (14).

    Abstract translation: 传感器组件包括远程数据集中器（RDC）（14）和光学驱动的换能器模块（OPTM）（12）。 RDC（14）沿着光纤（16）发送包括参数请求信号的第一光脉冲。 OPTM 12连接到光纤16，并包括光电二极管22，能量存储装置30，传感器36，处理器32和激光器24。 光电二极管（22）接收第一光脉冲，并且能量存储装置（30）由光电二极管（22）充电。 传感器（36），处理器（32）和激光器（24）通过使能量存储装置（30）放电而被供电。 传感器（36）感测由参数请求信号指定的参数。 处理器（32）从第一传感器（36）的输出生成信号包。 激光器将包括信号包的第二光脉冲沿着光纤传输到RDC（14）。

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