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    Multi-function air data sensing probe having an angle of attack vane
    3.
    发明公开
    Multi-function air data sensing probe having an angle of attack vane 有权
    Multifunktions-Luftdatensensor mitSchwenkflügel-Anstellwinkelsensor

    公开(公告)号：EP1491900A2

    公开(公告)日：2004-12-29

    申请号：EP04253847.0

    申请日：2004-06-28

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： Seidel, Greg A. ,  Cronin, Dennis J. ,  Mette, John H. ,  Koosmann, Mark R. ,  Schmitz, James A. ,  Fedele, John R. ,  Kromer, Dana A.

    IPC: G01P13/02 ,  G01P5/165

    CPC classification number: B64D43/02 ,  G01K13/028 ,  G01P5/165 ,  G01P13/025

    Abstract: A multi-function air data sensing probe has a strut that is mounted on an aircraft and extends laterally from the aircraft skin. The strut is supported on a base plate, and has a pitot pressure sensing tube at the outer end thereof, with a pitot port facing upstream, and also includes a passageway for total air temperature sensor including a forwardly facing inlet scoop that leads to a chamber in the strut that is laterally offset from the inlet scoop so that flow changes direction as it enters the chamber. The surface defining the change of direction between the scoop and the chamber is provided with bleed holes for bleeding off boundary layer air. A vane type air data sensor is mounted on a shaft that rotates freely and is supported on the strut, and is positioned to sense the relative air flow past the strut to determine changes of relative angles of such air flow. In addition, the strut has static pressure sensing ports on lateral sides thereof leading to a separate chamber on the interior of the strut.

    Abstract translation: 多功能空气数据传感探头具有安装在飞机上并从飞行器皮肤横向延伸的支柱。 支柱支撑在基板上，并且在其外端具有皮托管压力传感管，皮托口面向上游，并且还包括用于总空气温度传感器的通道，其包括朝向前方的入口勺，其通向腔室 在从入口勺侧向偏移的支柱中，使得流进入室时流动改变方向。 限定勺子和腔室之间的方向变化的表面设置有用于排出边界层空气的排放孔。 叶片型空气数据传感器安装在自由旋转并被支撑在支柱上的轴上，并且被定位成感测通过支柱的相对空气流以确定这种空气流的相对角度的变化。 此外，支柱在其横向侧上具有静态压力感测端口，其通向支柱内部的单独的室。

    Error detection and fault isolation for multi-function air data probes and systems
    4.
    发明公开
    Error detection and fault isolation for multi-function air data probes and systems 有权
    多功能机器人中的Fehlerdetektion和Fehlerisolation Luftdatensonde sowiezugehöriges系统

    公开(公告)号：EP1293784A2

    公开(公告)日：2003-03-19

    申请号：EP02256143.5

    申请日：2002-09-04

    Applicant: Rosemount Aerospace Inc.

    Inventor： Alwin, Steve F. ,  Cronin, Dennis J. ,  Foster, Roger D. ,  Amerson, Thomas D. ,  Skarohlid, Mark C.

    IPC: G01P13/02

    CPC classification number: G01P21/025 ,  G01P13/025

    Abstract: A method of detecting errors in air data sensing systems having multi-function probes being used in combinations to define probe systems includes a step (A) of, for each probe system, making a first prediction of an aircraft parameter as a function of local angles of attack at two member probes of the particular system, and making a second prediction of the aircraft parameter as a function of local pressure ratios at the two member probes of the particular system. A step (B) is performed in which, for each of the probe systems, the first and second predictions of the aircraft parameter are compared to determine whether the first and second predictions are within a predetermined threshold of each other. Then, a step (C) is performed in which, for each of the probe systems, if the first and second predictions of the aircraft parameter are not within the predetermined threshold of each other, then the particular probe system is identified as having a malfunctioning member probe.

    Abstract translation: 检测具有组合定义探测系统的多功能探测器的空气数据传感系统中的错误的方法包括：对于每个探测系统，对飞机参数的第一预测作为局部角度的函数进行步骤（A） 在特定系统的两个成员探针处的攻击，以及作为特定系统的两个成员探针处的局部压力比的函数的飞机参数的第二预测。 执行步骤（B），其中对于每个探测系统，比较飞行器参数的第一和第二预测以确定第一和第二预测是否在彼此的预定阈值内。 然后，执行步骤（C），其中对于每个探测系统，如果飞行器参数的第一和第二预测不在彼此的预定阈值内，则特定探测系统被识别为具有故障 成员探针。

    Sideslip correction for a multi-function three probe air data system
    7.
    发明公开
    Sideslip correction for a multi-function three probe air data system 有权
    对于具有三个探针的多官能Luftdatensytem侧滑角校正

    公开(公告)号：EP1256812A3

    公开(公告)日：2003-05-14

    申请号：EP02253069.5

    申请日：2002-04-30

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： Cronin, Dennis J. ,  Amerson, Thomas D.

    IPC: G01P13/02 ,  B64D43/02 ,  G01P5/16

    CPC classification number: G01P3/62 ,  G01C5/06 ,  G01P5/165 ,  G01P13/025

    Abstract: A multi-function probe system (14, 16, 18, 50, 70) that provides redundancy for measurements and compensates for effects of sideslip of an aircraft (10) includes at least two probes (14, 16) that are symmetrically located on the opposite sides of the aircraft, and a third probe (18, 50, 70) mounted on the centerline (20) of the aircraft (10) positioned to directly measure local sideslip, in one form (18, 50) of the third probe with ports (60, 62) that are positioned on opposite sides of the center plane of the aircraft. Each of the probes (14, 16, 18, 50, 70) includes self contained instrumentation (14D, 16D, 18D, 38) for providing signals indicating various pressures. The local angle of sideslip sensed by the third probe (18, 50, 70) is used as a compensation for pressure readings at either of the other probes (14, 16) for determining actual angle of attack, and static pressure.

    Method of reducing total temperature errors and multi-function probe implementing same
    8.
    发明公开
    Method of reducing total temperature errors and multi-function probe implementing same 有权
    一种用于减少在多官能探头整体温度误差和其实施方法

    公开(公告)号：EP1275947A2

    公开(公告)日：2003-01-15

    申请号：EP02254905.9

    申请日：2002-07-12

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： Cronin, Dennis J. ,  Alwin, Steve F.

    IPC: G01K13/02 ,  G01P13/02 ,  G01P5/165 ,  B64D43/02

    CPC classification number: G01K13/028 ,  B64D43/02 ,  G01K13/02 ,  G01P13/025

    Abstract: A method of generating, for an aircraft, a total air temperature compensated for recovery or deicing heater error includes measuring a total air temperature (MEASURED TAT 18) with a total air temperature probe. A local angle of attack for the total air temperature probe is determined (110). Then, a corrected total air temperature (CORRECTED TAT), compensated for recovery or deicing heater error, is generated (130) as a function of the measured total air temperature and the determined local angle of attack for the total air temperature probe.

    Abstract translation: 在飞机产生，为的试验方法中，总空气温度补偿恢复或除冰加热误差包括：测量总空气温度（TAT MEASURED 18），总的空气温度。 攻击的总空气温度探测器的局部角度确定性开采（110）。 然后，校正后的总空气温度（TAT CORRECTED），用于恢复或除冰加热误差补偿，则产生（130）根据所测量的总空气温度的函数，并且攻击的总空气温度探测器的确定性开采局部角度。

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