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1. 发明授权

US06609421B2 Sideslip correction for a multi-function three probe air data system 有权
公开(公告)号：US06609421B2
公开(公告)日：2003-08-26
申请号：US09850796
申请日：2001-05-08
申请人： Dennis J. Cronin , Thomas D. Amerson
发明人： Dennis J. Cronin , Thomas D. Amerson
IPC分类号： G01W100
CPC分类号： G01P3/62 , G01C5/06 , G01P5/165 , G01P13/025
摘要： A multi-function probe system that provides redundancy for measurements and compensates for effects of sideslip of an aircraft includes at least two probes that are symmetrically located on the opposite sides of the aircraft, and a third probe mounted on the centerline of the aircraft positioned to directly measure local sideslip with ports that are positioned on opposite sides of the center plane of the aircraft. Each of the probes includes self contained instrumentation for providing signals indicating various pressures. The local angle of sideslip sensed by the third probe is used as a compensation for pressure readings at either of the other probes for determining actual angle of attack, and static pressure.

2. 发明授权

US06761057B2 Error detection and fault isolation for multi-function air data probes and systems 有权
标题翻译：多功能空气数据探头和系统的错误检测和故障隔离
公开(公告)号：US06761057B2
公开(公告)日：2004-07-13
申请号：US09952043
申请日：2001-09-13
申请人： Dennis J. Cronin , Thomas D. Amerson , Roger D. Foster , Steve F. Alwin , Mark C. Skarohlid
发明人： Dennis J. Cronin , Thomas D. Amerson , Roger D. Foster , Steve F. Alwin , Mark C. Skarohlid
IPC分类号： G01C2500
CPC分类号： G01P21/025 , G01P13/025
摘要： 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.
摘要翻译：一种用于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误差的方法，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的步骤（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。

3. 发明授权

US06604029B2 Multi-function air data probes using neural network for sideslip compensation 有权
标题翻译：多功能空气数据探头采用神经网络进行侧滑补偿
公开(公告)号：US06604029B2
公开(公告)日：2003-08-05
申请号：US09851289
申请日：2001-05-08
申请人： Dennis J. Cronin , Roger D. Foster
发明人： Dennis J. Cronin , Roger D. Foster
IPC分类号： G06F1518
CPC分类号： G05B13/027 , B64D43/02 , G01P13/025
摘要： An air data sensing probe such as a multi-function probe includes a barrel having multiple pressure sensing ports for sensing multiple pressures. Instrumentation coupled to the pressure sensing ports provides electrical signals indicative of the pressures. An inertial navigation system input of the probe receives electrical signals indicative of inertial navigation data for the aircraft. A neural network of the probe receives as inputs the electrical signals indicative of the multiple pressures and the electrical signals indicative of the inertial navigation data. The neural network is trained or configured to provide as an output, electrical signals indicative of an air data parameter.
摘要翻译：诸如多功能探头的空气数据感测探头包括具有用于感测多个压力的多个压力感测端口的筒体。耦合到压力感测端口的仪器提供指示压力的电信号。探测器的惯性导航系统输入接收指示飞机的惯性导航数据的电信号。探头的神经网络接收表示多个压力的电信号和指示惯性导航数据的电信号作为输入。神经网络被训练或配置为提供指示空气数据参数的电信号作为输出。

4. 发明授权

US06941805B2 Multi-function air data sensing probe having an angle of attack vane 有权
标题翻译：具有迎角的多功能空气数据传感探头
公开(公告)号：US06941805B2
公开(公告)日：2005-09-13
申请号：US10606929
申请日：2003-06-26
申请人： Greg A. Seidel , Dennis J. Cronin , John H. Mette , Mark R. Koosmann , James A. Schmitz , John R. Fedele , Dana A. Kromer
发明人： Greg A. Seidel , Dennis J. Cronin , John H. Mette , Mark R. Koosmann , James A. Schmitz , John R. Fedele , Dana A. Kromer
IPC分类号： B64D43/02 , G01P5/165 , G01P13/02 , G01P13/00
CPC分类号： B64D43/02 , G01K13/028 , G01P5/165 , G01P13/025
摘要： 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.
摘要翻译：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，并且在其外端处具有皮托管压力感测管，皮托管端口面向上游，并且还包括用于总空气温度传感器的通道，其包括朝向入口勺通向腔室在从入口勺侧向偏移的支柱中，使得当其进入腔室时流动改变方向。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的轴上并被支撑在支柱上，并且被定位成感测通过支柱的相对气流，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。

5. 再颁专利

USRE39295E1 Ice detector configuration for improved ice detection at near freezing conditions 有权
标题翻译：冰检测器配置，用于在近冷冻条件下改进冰检测
公开(公告)号：USRE39295E1
公开(公告)日：2006-09-19
申请号：US10659678
申请日：2003-09-10
申请人： Dennis J. Cronin , Darren G. Jackson , David G. Owens
发明人： Dennis J. Cronin , Darren G. Jackson , David G. Owens
IPC分类号： G08B19/02
CPC分类号： G08B19/02 , B64D15/20
摘要： An ice detector for an aircraft comprises a strut and probe assembly, and it is positioned on the aircraft so that the pressure field around the ice detector causes a lower temperature region on the probe assembly compared to the aircraft. Ice will therefore form on the probe assembly before it forms on the aircraft to provide an early warning of icing conditions near freezing temperatures.
摘要翻译：用于飞行器的冰检测器包括支柱和探针组件，并且其位于飞行器上，使得与飞行器相比，冰探测器周围的压力场引起探针组件上的较低温度区域。因此，冰会在飞机上形成探针组件，以便在冰温附近提供结霜状况的早期预警。

6. 发明授权

US07031871B2 Sensor assembly for determining total temperature, static temperature and Mach number 有权
标题翻译：用于确定总温度，静态温度和马赫数的传感器组件
公开(公告)号：US07031871B2
公开(公告)日：2006-04-18
申请号：US10862068
申请日：2004-06-04
申请人： John A. Severson , Kenneth J. Freeman , Dennis J. Cronin
发明人： John A. Severson , Kenneth J. Freeman , Dennis J. Cronin
IPC分类号： G01K1/00
CPC分类号： G01K13/02 , G01K13/028
摘要： A temperature sensor is provided with at least two thermometers or temperature sensing elements that have different recovery factors, and which are in the same airflow. The recovery factors for the respective thermometers are determined for the sensor and stored in a memory of a processor. The temperature measured by each of the thermometers is provided to the processor, and the processor establishes ratios using the recovery factors and measured temperatures to determine total temperature and static temperature of the airflow in which the thermometers are placed.
摘要翻译：温度传感器设置有至少两个温度计或温度感测元件，其具有不同的恢复因子，并且处于相同的气流中。为传感器确定各温度计的恢复系数，并存储在处理器的存储器中。由每个温度计测量的温度被提供给处理器，并且处理器使用恢复因子和测量的温度建立比率，以确定放置温度计的气流的总温度和静态温度。

7. 发明授权

US06320511B1 Ice detector configuration for improved ice detection at near freezing conditions 有权
标题翻译：冰检测器配置，用于在近冷冻条件下改进冰检测
公开(公告)号：US06320511B1
公开(公告)日：2001-11-20
申请号：US09724101
申请日：2000-11-28
申请人： Dennis J. Cronin , Darren G. Jackson , David G. Owens
发明人： Dennis J. Cronin , Darren G. Jackson , David G. Owens
IPC分类号： G08B1902
CPC分类号： G08B19/02 , B64D15/20
摘要： An ice detector for an aircraft comprises a strut and probe assembly, and it is positioned on the aircraft so that the pressure field around the ice detector causes a lower temperature region on the probe assembly compared to the aircraft. Ice will therefore form on the probe assembly before it forms on the aircraft to provide an early warning of icing conditions near freezing temperatures.
摘要翻译：用于飞行器的冰检测器包括支柱和探针组件，并且其位于飞行器上，使得与飞行器相比，冰探测器周围的压力场引起探针组件上的较低温度区域。因此，冰会在飞机上形成探针组件，以便在冰温附近提供结霜状况的早期预警。

8. 发明授权

US07379839B2 Multi-function air data probes employing neural networks for determining local air data parameters 有权
标题翻译：使用神经网络确定局部空气数据参数的多功能空中数据探测器
公开(公告)号：US07379839B2
公开(公告)日：2008-05-27
申请号：US10328487
申请日：2002-12-23
申请人： Dennis J. Cronin , Karl G. Drutowski , Andrew P. Mack
发明人： Dennis J. Cronin , Karl G. Drutowski , Andrew P. Mack
IPC分类号： G01L7/00
CPC分类号： B64D43/02 , G01P13/025
摘要： An air data sensing probe or MFP includes a barrel having multiple pressure sensing ports for sensing multiple pressures. Instrumentation coupled to the pressure sensing ports provides electrical signals related to the multiple pressures. A neural network, coupled to the instrumentation, receives as inputs the electrical signals related to the multiple pressures, and in response, the neural network provides, as an output, electrical signals indicative of at least one local air data parameter for the air data sensing probe.
摘要翻译：空气数据感测探头或MFP包括具有用于感测多个压力的多个压力感测端口的筒体。耦合到压力感测端口的仪器提供与多个压力相关的电信号。耦合到仪器的神经网络接收与多个压力相关的电信号作为输入，并且作为响应，神经网络提供指示空气数据感测的至少一个局部空气数据参数的电信号作为输出探测。

9. 发明授权

US06594559B2 Iterative method of aircraft sideslip compensation for multi-function probe air data systems 有权
公开(公告)号：US06594559B2
公开(公告)日：2003-07-15
申请号：US09851485
申请日：2001-05-08
申请人： Steve F. Alwin , Dennis J. Cronin , Roger D. Foster
发明人： Steve F. Alwin , Dennis J. Cronin , Roger D. Foster
IPC分类号： G01C2100
CPC分类号： G05D1/0204
摘要： In an iterative method of determining aircraft flight data parameters using first and second multi-function probes, an assumed value of a first aircraft parameter is defined to be equal to an initial value. Using the assumed value of the first aircraft parameter together with the respective local angles of attack determined at first and second multi-function probes, first and second estimates of a second aircraft parameter are calculated and compared. If the first and second estimates of the second aircraft parameter are within tolerance of each other, then the first aircraft parameter is approximately equal to the assumed value, and the second aircraft parameter is determined from the first and second estimates. If the first and second estimates of the second aircraft parameter are not within tolerance of each other, then an iterative process is continued to correctly determine the first and second parameters.

10. 发明授权

US06543298B2 Method of reducing total temperature errors and multi-function probe implementing same 有权
标题翻译：减少总温度误差的方法和实现相同的多功能探头
公开(公告)号：US06543298B2
公开(公告)日：2003-04-08
申请号：US09905167
申请日：2001-07-13
申请人： Dennis J. Cronin , Steve F. Alwin
发明人： Dennis J. Cronin , Steve F. Alwin
IPC分类号： G01F146
CPC分类号： G01K13/028 , B64D43/02 , G01K13/02 , G01P13/025
摘要： A method of generating, for an aircraft, a total air temperature compensated for recovery or deicing heater error includes measuring a total air temperature with a total air temperature probe. A local angle of attack for the total air temperature probe is determined. Then, a corrected total air temperature, compensated for recovery or deicing heater error, is generated as a function of the measured total air temperature and the determined local angle of attack for the total air temperature probe.
摘要翻译：为航空器生成补偿回收或除冰加热器误差的总空气温度的方法包括用总空气温度探头测量总空气温度。确定总空气温度探头的局部迎角。然后，根据测得的总空气温度和确定的总空气温度探头的局部迎角产生校正的总空气温度，补偿恢复或除冰加热器误差。

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