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    Total air temperature probe providing a secondary sensor measurement chamber
    1.
    发明授权
    Total air temperature probe providing a secondary sensor measurement chamber 失效
    提供次级传感器测量室的总气温探头

    公开(公告)号：US07174782B2

    公开(公告)日：2007-02-13

    申请号：US10947546

    申请日：2004-09-22

    申请人： Paul A. Ice

    发明人： Paul A. Ice

    IPC分类号： G01F1/68

    CPC分类号： G01K13/028 ,  G01K13/02

    摘要： A total air temperature sensor probe samples the air stream surrounding an aircraft in flight, and includes a duct carrying a fluid flow a portion of which is diverted to a primary chamber mounting a total air temperature sensor. A secondary chamber has a secondary sensor for sensing a different property of a sampled air stream. The secondary chamber is open to receive air flow from passageways in the total air temperature probe.

    摘要翻译： 总空气温度传感器探头对飞行中的飞行器周围的空气流进行采样，并且包括承载流体流的管道，其一部分被转移到安装总空气温度传感器的主室。 次级室具有用于感测采样空气流的不同性质的次级传感器。 二级室打开以接收来自总空气温度探头中的通道的气流。

    Total air temperature probe providing improved anti-icing performance and reduced deicing heater error
    2.
    发明授权
    Total air temperature probe providing improved anti-icing performance and reduced deicing heater error 有权
    总空气温度探头提供更好的防冰性能，减少除冰加热器误差

    公开(公告)号：US06840672B2

    公开(公告)日：2005-01-11

    申请号：US10601760

    申请日：2003-06-23

    申请人： Paul A. Ice ,  Charles R. Willcox

    发明人： Paul A. Ice ,  Charles R. Willcox

    IPC分类号： G01K13/02 ,  G01K1/16 ,  G01K1/18

    CPC分类号： G01K13/028 ,  G01K13/02

    摘要： A total air temperature (TAT) probe for measuring TAT includes an inlet scoop which receives airflow from free stream airflow moving toward the inlet scoop from a first direction. A first portion of the airflow entering the inlet scoop exits the probe through a main exit channel. A second portion of the airflow enters a TAT sensor flow passage, which extends longitudinally along an axis. This axis is oriented to form an angle of less than 90 degrees with the first direction from which the free stream airflow moves toward the inlet scoop. A sensor assembly extends longitudinally in the sensor flow passage and measures a total air temperature of airflow through the sensor flow passage. By increasing the angle through which the internal air turns, better inertial extraction of ice and water particles is realized. As a result, sensor clogging from accreted ice is significantly reduced. A second improvement is achieved by repositioning the sensor element to be more in-line with the internal airflow direction. This helps lower DHE by minimizing heated boundary layer spillage onto the sensing element.

    摘要翻译： 用于测量TAT的总空气温度（TAT）探针包括入口勺，其从第一方向接收从流入气流向入口勺移动的气流。 进入入口勺的气流的第一部分通过主出口通道离开探头。 气流的第二部分进入TAT传感器流动通道，其沿轴线纵向延伸。 该轴被定向成与自由流气流从入口勺移动的第一方向形成小于90度的角度。 传感器组件在传感器流动通道中纵向延伸并且测量通过传感器流动通道的气流的总空气温度。 通过增加内部空气转动的角度，实现了冰和水颗粒的较好的惯性提取。 结果，传感器堵塞从积冰显着减少。 通过将传感器元件重新定位成与内部气流方向更一致地实现第二改进。 这有助于通过最小化加热的边界层溢出到感测元件来降低DHE。

    Total air temperature probe providing a secondary sensor measurement chamber
    3.
    发明授权
    Total air temperature probe providing a secondary sensor measurement chamber 失效
    提供次级传感器测量室的总气温探头

    公开(公告)号：US07370526B1

    公开(公告)日：2008-05-13

    申请号：US11614591

    申请日：2006-12-21

    申请人： Paul A. Ice

    发明人： Paul A. Ice

    IPC分类号： G01F1/68

    CPC分类号： G01K13/02 ,  G01K13/028 ,  G01P5/16 ,  G01P5/165 ,  G01P13/025

    摘要： A total air temperature sensor probe samples the air stream surrounding an aircraft in flight, and includes a duct carrying a fluid flow a portion of which is diverted to a primary chamber mounting a total air temperature sensor. A secondary chamber has a secondary sensor for sensing a different property of a sampled air stream. The secondary chamber is open to receive air flow from passageways in the total air temperature probe.

    摘要翻译： 总空气温度传感器探头对飞行中的飞行器周围的空气流进行采样，并且包括承载流体流的管道，其一部分被转移到安装总空气温度传感器的主室。 次级室具有用于感测采样空气流的不同性质的次级传感器。 二级室打开以接收来自总空气温度探头中的通道的气流。

    Total air temperature probe providing improved anti-icing performance and reduced deicing heater error
    6.
    发明授权
    Total air temperature probe providing improved anti-icing performance and reduced deicing heater error 有权

    公开(公告)号：US06609825B2

    公开(公告)日：2003-08-26

    申请号：US09960594

    申请日：2001-09-21

    申请人： Paul A. Ice ,  Charles R. Willcox

    发明人： Paul A. Ice ,  Charles R. Willcox

    IPC分类号： G01K1302

    CPC分类号： G01K13/028 ,  G01K13/02

    摘要： A total air temperature probe positionable on a surface of an aircraft for measuring total air temperature includes an inlet scoop which receives airflow from free stream airflow moving toward the inlet scoop from a first direction. A first portion of the airflow entering the inlet scoop exits the probe through a main exit channel. A second portion of the airflow enters a TAT sensor flow passage, which extends longitudinally along an axis. This axis is oriented to form an angle of less than 90 degrees with the first direction from which the free stream airflow moves toward the inlet scoop. A sensor assembly extends longitudinally in the sensor flow passage and measures a total air temperature of airflow through the sensor flow passage. By increasing the angle through which the internal air turns, better inertial extraction of ice and water particles is realized. As a result, sensor clogging from accreted ice is significantly reduced. A second improvement is achieved by repositioning the sensor element to be more in-line with the internal air flow direction. This helps lower DHE by minimizing heated boundary layer spillage onto the sensing element.

    Active heater control circuit and method used for aerospace probes
    9.
    发明授权
    Active heater control circuit and method used for aerospace probes 有权
    用于航空航天探头的主动加热器控制电路和方法

    公开(公告)号：US06414282B1

    公开(公告)日：2002-07-02

    申请号：US09704158

    申请日：2000-11-01

    申请人： Paul A. Ice ,  Charles R. Willcox

    发明人： Paul A. Ice ,  Charles R. Willcox

    IPC分类号： H05B102

    CPC分类号： G05D23/1913

    摘要： An active heater control circuit for a deicing heater on a probe mounted on an aircraft, such as a pitot pressure sensing probe, a pitot-static pressure sensing probe, a total air temperature sensor, or engine inlet probe, controls power to the heater through a switch. When activated the switch sends electrical power to the heater until the probe temperature reaches a desired set point. A feature of the invention is an override pulse, which independently activates the switch to provide power to the heater at a selected period and duty cycle such that the aircraft current monitoring circuit receives current sufficiently often to avoid triggering a false heater failure alarm even when the probe temperature has reached its control set point. This feature allows the use of probes incorporating active heat control on existing aircraft configured for older probes having simple nickel-based resistive heater control.

    摘要翻译： 安装在飞机上的探头上的用于除冰加热器的主动加热器控制电路，例如皮托压力感测探头，皮托静压感测探头，总空气温度传感器或发动机入口探针，通过 一个开关 当激活时，开关向加热器发送电力，直到探头温度达到所需的设定点。 本发明的特征是超控脉冲，其独立地激活开关以在选定的周期和占空比下向加热器供电，使得飞行器电流监测电路充分经常地接收电流，以避免触发假加热器故障警报，即使当 探头温度已达到其控制设定值。 该功能允许使用在现有飞机上配置主动热控制的探头，配置为具有简单的镍基电阻加热器控制的较老探头。