-
1.发明授权Error detection and fault isolation for multi-function air data probes and systems 有权错误检测和故障隔离在多功能空气数据探头和相关的系统
公开(公告)号：EP1293784B1
公开(公告)日：2008-11-05
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
-
2.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.
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。
-
3.发明公开Error detection and fault isolation for multi-function air data probes and systems 有权错误检测和故障隔离在多功能空气数据探头和相关的系统
公开(公告)号：EP1293784A3
公开(公告)日：2004-01-07
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.
-
4.发明公开Iterative method of aircraft sideslip compensation for multi-function probe air data systems 有权用于与多功能空气数据探头系统的飞行器的漂移补偿迭代方法
公开(公告)号：EP1256862A2
公开(公告)日：2002-11-13
申请号：EP02253056.2
申请日：2002-04-30
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Alwin, Steve F. , Foster, Roger D. , Cronin, Dennis J.
IPC: G05D1/02
CPC classification number: G05D1/0204
Abstract: In an iterative method of determining aircraft flight data parameters using first and second multifunction 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 multifunction 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.
Abstract translation: 在使用第一，第二多功能探针（14,16,18）与第一飞行器参数的假定值的确定性采矿飞机飞行数据和参数的迭代方法被定义为在初始值等于。 与攻击确定性，在第一和第二多功能探头，第二架飞机参数的第一和第二估计开采的respectivement局部角度一起使用的第一架飞机参数的假定值计算和比较。 如果第二飞行器参数的第一和第二估计海誓山盟公差之内，则第一飞行器参数是近似等于假定值，以及从所述第一和第二估计的第二飞行器参数确定性开采。 如果第二飞机参数的第一和第二估计不是海誓山盟的容差范围内，那么迭代过程中被继续正确确定性矿山第一和第二参数。
-
5.发明公开Iterative method of aircraft sideslip compensation for multi-function probe air data systems 有权用于与多功能空气数据探头系统的飞行器的漂移补偿迭代方法
公开(公告)号：EP1256862A3
公开(公告)日：2005-06-15
申请号：EP02253056.2
申请日：2002-04-30
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Alwin, Steve F. , Foster, Roger D. , Cronin, Dennis J.
CPC classification number: G05D1/0204
Abstract: In an iterative method of determining aircraft flight data parameters using first and second multifunction probes (14,16,18), 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 multifunction 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.
-
Patent Agency Ranking
公开(公告)号：EP1237005A3
公开(公告)日：2004-01-14
申请号：EP02251402.0
申请日：2002-02-28
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Bachinski, Thomas J. , Alwin, Steve F. , Rach, Eric J.
CPC classification number: G01K13/028 , G01C5/005 , G01P5/165 , G01P13/025 , G01P15/18 , G01S19/15 , G01S19/36 , G01S19/49
Abstract: A smart probe assembly (16,20) for an aircraft 12, includes pressure sensing ports (16C,20C) for sensing pressures indicating angle of attack, static pressure and pitot pressure, a circuit housing (28,30) mounted on said probe includes cards for a central processing unit (38), and also includes a global positioning satellite receiver (62). An antenna (64) for the global positioning satellite receiver (62) is mounted adjacent to the probe (16,20), on a mounting plate (18) so that the antenna (64) is protruding from the aircraft (12) without cutting an additional hole in the aircraft skin (14). The inputs from the global positioning satellite receiver (62) are used for providing various flight performance information.
-
公开(公告)号：EP1237005A2
公开(公告)日：2002-09-04
申请号：EP02251402.0
申请日：2002-02-28
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Bachinski, Thomas J. , Alwin, Steve F. , Rach, Eric J.
CPC classification number: G01K13/028 , G01C5/005 , G01P5/165 , G01P13/025 , G01P15/18 , G01S19/15 , G01S19/36 , G01S19/49
Abstract: A smart probe assembly (16,20) for an aircraft 12, includes pressure sensing ports (16C,20C) for sensing pressures indicating angle of attack, static pressure and pitot pressure, a circuit housing (28,30) mounted on said probe includes cards for a central processing unit (38), and also includes a global positioning satellite receiver (62). An antenna (64) for the global positioning satellite receiver (62) is mounted adjacent to the probe (16,20), on a mounting plate (18) so that the antenna (64) is protruding from the aircraft (12) without cutting an additional hole in the aircraft skin (14). The inputs from the global positioning satellite receiver (62) are used for providing various flight performance information.
Abstract translation: 用于飞行器12的智能探针组件（16,20）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（16C，20C），安装在所述探头上的电路壳体（28,30）包括 用于中央处理单元（38）的卡，并且还包括全球定位卫星接收器（62）。 用于全球定位卫星接收器（62）的天线（64）在探针（16,20）附近安装在安装板（18）上，使得天线（64）从飞行器（12）突出而不切割 在飞机皮肤上有一个额外的孔（14）。 来自全球定位卫星接收机（62）的输入用于提供各种飞行性能信息。
-
公开(公告)号：EP1936386B1
公开(公告)日：2012-05-30
申请号：EP07254949.6
申请日：2007-12-19
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Alwin, Steve F. , Liffrig, Ronald Fritz , Sandnas, Matthew L.
CPC classification number: B64C13/16 , B64D43/02 , G01K13/028
-
9.发明授权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：EP1275947B1
公开(公告)日：2008-07-02
申请号：EP02254905.9
申请日：2002-07-12
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Cronin, Dennis J. , Alwin, Steve F.
CPC classification number: G01K13/028 , B64D43/02 , G01K13/02 , G01P13/025
-
10.发明授权Iterative method of aircraft sideslip compensation for multi-function probe air data systems 有权用于与多功能空气数据探头系统的飞行器的漂移补偿迭代方法
公开(公告)号：EP1256862B1
公开(公告)日：2007-10-10
申请号：EP02253056.2
申请日：2002-04-30
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Alwin, Steve F. , Foster, Roger D. , Cronin, Dennis J.
CPC classification number: G05D1/0204
-
-
-
-
-
-
-
-
-
Search Results
15
records
(took 0.009 seconds)
