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    DETECTING ICE PARTICLES
    1.
    发明申请
    DETECTING ICE PARTICLES 审中-公开
    检测冰颗粒

    公开(公告)号：WO2008051673A2

    公开(公告)日：2008-05-02

    申请号：PCT/US2007079328

    申请日：2007-09-24

    Applicant: ROSEMOUNT AEROSPACE INC ,  SEVERSON JOHN A ,  JACKSON DARREN ,  HANSEN MATT

    Inventor： SEVERSON JOHN A ,  JACKSON DARREN ,  HANSEN MATT

    CPC classification number: B64D15/20 ,  G08B19/02

    Abstract: Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit.

    Abstract translation: 本文公开了用于检测冰颗粒积聚的系统和方法。 在一个示例性实施例中，描述了一种用于检测冰的方法，其中测量加热导管的内部体积内的参数。 该方法还包括基于在加热管道的内部体积内测量的参数检测冰颗粒的积聚的存在。

    INTEGRATED TOTAL TEMPERATURE PROBE SYSTEM
    3.
    发明申请
    INTEGRATED TOTAL TEMPERATURE PROBE SYSTEM 审中-公开
    整体温度探针系统

    公开(公告)号：WO0142751A2

    公开(公告)日：2001-06-14

    申请号：PCT/US0042705

    申请日：2000-12-08

    Applicant: ROSEMOUNT AEROSPACE INC

    Inventor： KROMER DANA A ,  SEVERSON JOHN A

    IPC: G01K13/02 ,  G01K

    CPC classification number: G01K13/028 ,  G01K13/02

    Abstract: A smart probe system (10) for an aircraft receives an input from a heated total air temperature sensor (24). When on the ground, the heater (28) for the total air temperature probe (24) is cycled so that when a preselected temperature is indicated by the temperature sensing element (30) in the total air temperature probe (24), the heater power is turned off, and as the total air temperature probe (24) cools, changes in indicated temperature from the temperature sensing element (30) are measured and the changes analyzed and used for determining outside air temperature. The outside air temperature can be calculated by determining the rate of change in the temperature while the probe (24) cools. A complimentary method is to determine when the indicated temperature stabilizes, after the heater (28) is turned off, and deriving outside air temerature from the stabilized temperature signal from the temperature sensing element (30).

    Abstract translation: 用于飞机的智能探测系统（10）接收来自加热的总空气温度传感器（24）的输入。 当在地面上时，用于总空气温度探测器（24）的加热器（28）被循环，使得当在总空气温度探测器（24）中由温度感测元件（30）指示预选温度时，加热器功率 被关闭，并且当总空气温度探测器（24）冷却时，测量来自温度感测元件（30）的指示温度的变化并分析变化并用于确定外部空气温度。 外部空气温度可以通过确定探头（24）冷却时温度的变化率来计算。 一种免费的方法是在加热器（28）关闭之后确定指示温度何时稳定，并根据来自温度感测元件（30）的稳定温度信号导出外部空气温度。

    THERMAL ICING CONDITIONS DETECTOR
    4.
    发明专利
    THERMAL ICING CONDITIONS DETECTOR 未知

    公开(公告)号：CA2450062A1

    公开(公告)日：2004-05-19

    申请号：CA2450062

    申请日：2003-11-18

    Applicant: ROSEMOUNT AEROSPACE INC

    Inventor： SEVERSON JOHN A

    IPC: B64D15/20 ,  G08B19/02 ,  G01K3/00 ,  G01W1/00 ,  G01W1/02 ,  G01K7/16

    Abstract: A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present.

    6.
    发明专利
    未知

    公开(公告)号：DE602005001882T2

    公开(公告)日：2008-05-08

    申请号：DE602005001882

    申请日：2005-04-13

    Applicant: ROSEMOUNT AEROSPACE INC

    Inventor： SEVERSON JOHN A

    IPC: G01K13/02

    Abstract: The present invention relates to providing a temperature sensing probe (12,55) that is mountable on an aircraft (10) and includes a thermometer or temperature sensing element (38,57) for sensing temperature of airflow. A heater (35,35B) is provided on the probe to bias the temperature sensed by the thermometer or temperature sensing element (38,57), in a manner such that the temperature measured is at a substantially known offset from the static temperature surrounding the temperature sensing probe (12,55). Control of the offset can be achieved by regulating airflow or heat provided. The heating effect is controlled to be a substantially equal and opposite match to the decreased total temperature resulting from lower airspeed or decreased airflow. In this manner, the thermometer or temperature sensing element (38,57) will essentially operate at a fixed offset above static temperature, that is the temperature in undisturbed air in which the aircraft (10) is operating, over a fairly wide range of flow rates.

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