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1. 发明授权

US08620495B2 Air data stall protection system 有权
标题翻译：空中数据失速保护系统
公开(公告)号：US08620495B2
公开(公告)日：2013-12-31
申请号：US11958791
申请日：2007-12-18
申请人： Steve F. Alwin , Ronald Fritz Liffrig , Mathew L. Sandnas
发明人： Steve F. Alwin , Ronald Fritz Liffrig , Mathew L. Sandnas
IPC分类号： G05D1/08
CPC分类号： B64C13/16 , B64D43/02 , G01K13/028
摘要： An electronic multi-function probe (MFP) is provided for positioning adjacent an aircraft skin. The electronic MFP includes a plurality of pressure sensing ports and an electronics housing. Positioned within the electronics housing are air data processing circuitry and stall protection system processing circuitry. The air data processing circuitry is configured to generate air data parameters, including airspeed and altitude, as a function of pressures at the plurality of pressure sensing ports. The stall protection system processing circuitry of the electronic MFP is configured to detect stall conditions as a function of angle of attack and at least one air data parameter from the air data processing circuitry, and to generate stall protection system outputs indicative of the detected stall conditions.
摘要翻译：提供电子多功能探测器（MFP）用于定位在飞行器皮肤附近。电子MFP包括多个压力传感端口和电子设备外壳。位于电子设备外壳内的是空气数据处理电路和失速保护系统处理电路。空气数据处理电路被配置为产生空气数据参数，包括空速和高度，作为多个压力感测端口处的压力的函数。电子MFP的失速保护系统处理电路被配置为根据迎角和来自空中数据处理电路的至少一个空气数据参数来检测失速状况，并产生指示检测到的失速条件的失速保护系统输出。

2. 发明申请

US20080147255A1 Air Data Stall Protection System 有权
标题翻译：空中数据失速保护系统
公开(公告)号：US20080147255A1
公开(公告)日：2008-06-19
申请号：US11958791
申请日：2007-12-18
申请人： Steve F. Alwin , Ronald Fritz Liffrig , Mathew L. Sandnas
发明人： Steve F. Alwin , Ronald Fritz Liffrig , Mathew L. Sandnas
IPC分类号： B64C19/00
CPC分类号： B64C13/16 , B64D43/02 , G01K13/028
摘要： An electronic multi-function probe (MFP) is provided for positioning adjacent an aircraft skin. The electronic MFP includes a plurality of pressure sensing ports and an electronics housing. Positioned within the electronics housing are air data processing circuitry and stall protection system processing circuitry. The air data processing circuitry is configured to generate air data parameters, including airspeed and altitude, as a function of pressures at the plurality of pressure sensing ports. The stall protection system processing circuitry of the electronic MFP is configured to detect stall conditions as a function of angle of attack and at least one air data parameter from the air data processing circuitry, and to generate stall protection system outputs indicative of the detected stall conditions.
摘要翻译：提供电子多功能探测器（MFP）用于定位在飞行器皮肤附近。电子MFP包括多个压力传感端口和电子设备外壳。位于电子设备外壳内的是空气数据处理电路和失速保护系统处理电路。空气数据处理电路被配置为产生空气数据参数，包括空速和高度，作为多个压力感测端口处的压力的函数。电子MFP的失速保护系统处理电路被配置为根据迎角和来自空中数据处理电路的至少一个空气数据参数来检测失速状态，并产生指示检测到的失速条件的失速保护系统输出。

3. 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。

4. 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.

5. 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。

6. 发明授权

US06452542B1 Integrated flight management system 失效
标题翻译：综合飞行管理系统
公开(公告)号：US06452542B1
公开(公告)日：2002-09-17
申请号：US09798439
申请日：2001-03-02
申请人： Thomas J. Bachinski , Steve F. Alwin , Eric J. Rach
发明人： Thomas J. Bachinski , Steve F. Alwin , Eric J. Rach
IPC分类号： G01S502
CPC分类号： G01K13/028 , G01C5/005 , G01P5/165 , G01P13/025 , G01P15/18 , G01S19/15 , G01S19/36 , G01S19/49
摘要： A smart probe assembly for an aircraft includes pressure sensing ports for sensing pressures indicating angle of attack, static pressure and pitot pressure, a circuit housing mounted on said probe includes cards for a central processing unit, and also includes a global positioning satellite receiver. An antennae for the global positioning satellite receiver is mounted adjacent to the probe, on a mounting plate so that the antennae is protruding from the aircraft without cutting an additional hole in the aircraft skin, the inputs from the global positioning satellite are used for providing various flight performance information.
摘要翻译：用于飞行器的智能探针组件包括用于感测指示迎角，静压和皮托托压力的压力的压力感测端口，安装在所述探针上的电路壳体包括用于中央处理单元的卡，并且还包括全球定位卫星接收器。用于全球定位卫星接收机的天线安装在探头附近安装在安装板上，使得天线从飞行器突出而不在飞行器皮肤上切割另外的孔，来自全球定位卫星的输入用于提供各种飞行性能信息。

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