-
1.发明授权Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals 有权基于综合GNSS /惯性混合滤波器残差的姿态故障检测系统和方法公开(公告)号：US09593962B2
公开(公告)日：2017-03-14
申请号：US14564359
申请日：2014-12-09
Applicant: Honeywell International Inc.
Inventor： Mats Anders Brenner , Mark A. Ahlbrecht , John R. Morrison
CPC classification number: G01C23/005 , B64D47/00 , G05D1/0077 , G05D1/0808 , G07C5/0808
Abstract: Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals are provided. In one embodiment, a fault detection system for aircraft attitude measurement system comprises: a sensor monitor coupled to a first inertial measurement unit, the sensor monitor comprising: a navigation error model for the first inertial measurement unit, the model configured to model a plurality of error states including at least an attitude error state vector, an velocity error state vector, and a position error state vector determined from data generated by the first inertial measurement unit; and a propagator-estimator configured to propagate and update error states based on GNSS data; and a residual evaluator configured to input measurement error residual values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the measurement error residual values exceed a threshold.
Abstract translation: 提供了基于综合GNSS /惯性混合滤波器残差的姿态故障检测系统和方法。 在一个实施例中，用于飞行器姿态测量系统的故障检测系统包括：传感器监测器，耦合到第一惯性测量单元，所述传感器监测器包括：用于所述第一惯性测量单元的导航误差模型，所述模型被配置为对多个 误差状态至少包括由第一惯性测量单元产生的数据确定的姿态误差状态矢量，速度误差状态矢量和位置误差状态矢量; 以及传播者估计器，被配置为基于GNSS数据传播和更新错误状态; 以及残差评估器，被配置为输入由所述传播器估计器生成的测量误差残差值，其中当所述测量误差残差值超过阈值时，所述残差评估器输出报警信号。
-
2.发明申请SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION IN ONE OR MORE INERTIAL MEASUREMENT UNITS 有权一个或多个惯性测量单位中的态度故障检测的系统和方法公开(公告)号：US20160290825A1
公开(公告)日：2016-10-06
申请号：US14563597
申请日：2014-12-08
Applicant: Honeywell International Inc.
Inventor： Mats Anders Brenner , John R. Morrison
CPC classification number: G01C23/005 , G01C21/165 , G01S19/47 , G01S19/54
Abstract: Systems and methods for attitude fault detection in an inertial measurement unit (IMU) are disclosed. In one embodiment, an avionics system comprises: an IMU configured to produce a calculated pitch solution, a calculated roll solution, or both; a monitor coupled to the IMU and configured to produce an estimated pitch solution, an estimated roll solution, or both; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and a display device communicatively coupled to the comparator; wherein the display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.
Abstract translation: 公开了惯性测量单元（IMU）中姿态故障检测的系统和方法。 在一个实施例中，航空电子系统包括：IMU，被配置为产生计算的俯仰方案，计算出的滚动解或两者; 耦合到IMU并被配置为产生估计的俯仰方案，估计的解决方案或两者的监视器; 比较器，其中所述比较器确定所计算的间距溶液与所估计的间距溶液之间的差，所计算的辊溶液与所估计的辊溶液之间的差或两者; 以及通信地耦合到所述比较器的显示装置; 其中当所计算出的俯仰解和估计俯仰解之间的差大于俯仰阈值时，或当所计算的滚动方案与估计的滚动方向之间的差大于滚动时，显示装置从比较器接收警告消息 阈值或两者。
-
公开(公告)号：US20160107761A1
公开(公告)日：2016-04-21
申请号：US14575762
申请日：2014-12-18
Applicant: Honeywell International Inc.
Inventor： Mark A. Ahlbrecht , Michael R. Ibis , John R. Morrison
Abstract: Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution; an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.
Abstract translation: 提供了用于隔离姿态故障的系统和方法。 在一个实施例中，姿态完整性和显示系统包括显示系统，其包括显示第一姿态解决方案的主系统和显示第二姿势解决方案的备用系统; 一种姿态完整性系统，其产生从姿态解决方案数据源的测量结果计算的姿态完整性（AI）解决方案，包括航空器侧倾和俯仰的AI解决方案，数据源提供与惯性传感器飞行仪器产生的任何数据无关并且不显示的数据 在主系统或备用系统上; 以及姿态监视器，其将第一解决方案与第二解决方案进行比较。 当第一个解决方案偏离第二个解决方案超过一个阈值时，监视器在显示系统上识别第一个或第二个解决方案中的哪一个是基于哪个与AI解决方案有较大的偏差。
-
4.发明申请SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION BASED ON AIR DATA AND AIRCRAFT CONTROL SETTINGS 有权基于空气数据和飞机控制设置的姿态故障检测系统与方法公开(公告)号：US20160102994A1
公开(公告)日：2016-04-14
申请号：US14564344
申请日：2014-12-09
Applicant: Honeywell International Inc.
Inventor： Mats Anders Brenner , John R. Morrison , Danny Thomas Kimmel , Jay Joseph Hansen
CPC classification number: G01C23/005 , B64D45/00 , G05D1/0077 , G05D1/0808 , G07C5/0808
Abstract: Systems and methods for attitude fault detection based on air data and aircraft control settings are provided. In one embodiment, a sensor monitor for an aircraft attitude measurement system comprises: an aircraft model configured to model a plurality of states, the plurality of states including at least an aircraft attitude state, an aircraft velocity state, a sink rate error state, and a wind velocity state; a propagator-estimator configured to utilize the plurality of states of the aircraft model to process air data measurements and attitude measurements from a first inertial measurement unit of the aircraft attitude measurement system; and a residual evaluator configured to input residual error values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the residual error values exceed a predetermined statistical threshold.
Abstract translation: 提供了基于空中数据和飞机控制设置的姿态故障检测的系统和方法。 在一个实施例中，用于飞行器姿态测量系统的传感器监视器包括：飞行器模型，被配置为对多个状态建模，所述多个状态至少包括飞机姿态，飞行器速度状态，下沉速率误差状态和 风速状态; 传播器估计器，被配置为利用飞行器模型的多个状态来处理来自飞行器姿态测量系统的第一惯性测量单元的空气数据测量和姿态测量; 以及残差评估器，被配置为输入由所述传播器估计器生成的残差误差值，其中当所述残差误差值超过预定的统计阈值时，所述残差评估器输出报警信号。
-
公开(公告)号：US10921153B2
公开(公告)日：2021-02-16
申请号：US16153416
申请日：2018-10-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Sanju Kuriakose , Sriram P R , John R. Morrison , Mark Ahlbrecht
Abstract: Methods, apparatuses and systems for use of a magnetometer calibration (MAG-CAL) application to calibrate a magnetometer while an aircraft is in-flight including: generating a MAG-CAL calculated pattern based on a set of aircraft parameters for the in-air magnetometer calibration, the set of aircraft parameters at least comprise: speed, bank angle, altitude and position of the aircraft; generating a set of waypoints that define a calibration flight path corresponding to the MAG-CAL calculated pattern; Configuring the calibration flight path of the MAG-CAL calculated pattern to be part of the original flight path of the in-flight aircraft to enable the aircraft while flying the original flight to proceed in part on the calibration flight path corresponding to the MAG-CAL calculated pattern; and enabling the aircraft to deviate while in-flight from the original flight path to the calibration flight path to enable a sufficient level of calibration for accurate magnetometer operation.
-
Patent Agency Ranking
公开(公告)号：US09688416B2
公开(公告)日：2017-06-27
申请号：US14575762
申请日：2014-12-18
Applicant: Honeywell International Inc.
Inventor： Mark A. Ahlbrecht , Michael R. Ibis , John R. Morrison
Abstract: Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution; an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.
-
公开(公告)号：US09671226B2
公开(公告)日：2017-06-06
申请号：US14573657
申请日：2014-12-17
Applicant: Honeywell International Inc.
Inventor： John R. Morrison , Vibhor L. Bageshwar , Ruth Dagmar Kreichauf , Zdenek Kana
CPC classification number: G01C17/38 , G01R33/0035
Abstract: A method of magnetic sensor calibration for aircraft comprises obtaining attitude data, heading angle data, position data, and date information; inputting the position data and date into an earth magnetic field (EMF) model and into an EMF model correction map; inputting the attitude and heading angle data into a NOLL to body frame transformation module; outputting an EMF model vector from the EMF model; outputting an EMF correction vector from the EMF model correction map; compensating the EMF model vector with the EMF correction vector to produce a corrected EMF model vector; inputting the corrected EMF model vector into the transformation module; inputting magnetic field measurements data into a calibration processing unit; inputting true earth magnetic field data from the transformation module into the processing unit; computing compensation coefficients in the processing unit based on the magnetic field measurements and the true earth magnetic field; and storing the compensation coefficients.
-
公开(公告)号：US20160178371A1
公开(公告)日：2016-06-23
申请号：US14573657
申请日：2014-12-17
Applicant: Honeywell International Inc.
Inventor： John R. Morrison , Vibhor L. Bageshwar , Ruth Dagmar Kreichauf , Zdenek Kana
CPC classification number: G01C17/38 , G01R33/0035
Abstract: A method of magnetic sensor calibration for aircraft comprises obtaining attitude data, heading angle data, position data, and date information; inputting the position data and date into an earth magnetic field (EMF) model and into an EMF model correction map; inputting the attitude and heading angle data into a NOLL to body frame transformation module; outputting an EMF model vector from the EMF model; outputting an EMF correction vector from the EMF model correction map; compensating the EMF model vector with the EMF correction vector to produce a corrected EMF model vector; inputting the corrected EMF model vector into the transformation module; inputting magnetic field measurements data into a calibration processing unit; inputting true earth magnetic field data from the transformation module into the processing unit; computing compensation coefficients in the processing unit based on the magnetic field measurements and the true earth magnetic field; and storing the compensation coefficients.
Abstract translation: 飞行器的磁传感器校准方法包括获取姿态数据，航向角数据，位置数据和日期信息; 将位置数据和日期输入到地磁场（EMF）模型中并进入EMF模型校正图; 将姿态和方位角数据输入到车体帧变换模块的NOLL中; 从EMF模型输出EMF模型向量; 从EMF模型校正图中输出EMF校正矢量; 用EMF校正向量补偿EMF模型向量以产生校正的EMF模型向量; 将校正的EMF模型向量输入到变换模块中; 将磁场测量数据输入校准处理单元; 将来自变换模块的真实地磁场数据输入到处理单元; 基于磁场测量和真实的地球磁场计算处理单元中的补偿系数; 并存储补偿系数。
-
9.发明授权公开(公告)号：US09880021B2
公开(公告)日：2018-01-30
申请号：US14563597
申请日：2014-12-08
Applicant: Honeywell International Inc.
Inventor： Mats Anders Brenner , John R. Morrison
CPC classification number: G01C23/005 , G01C21/165 , G01S19/47 , G01S19/54
Abstract: Systems and methods for attitude fault detection in an inertial measurement unit (IMU) are disclosed. In one embodiment, an avionics system comprises: an IMU configured to produce a calculated pitch solution, a calculated roll solution, or both; a monitor coupled to the IMU and configured to produce an estimated pitch solution, an estimated roll solution, or both; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and a display device communicatively coupled to the comparator; wherein the display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.
-
公开(公告)号：US09719782B2
公开(公告)日：2017-08-01
申请号：US14599027
申请日：2015-01-16
Applicant: Honeywell International Inc.
Inventor： John R. Morrison , Douglas Mark Weed , Mark Hickey
CPC classification number: G01C9/005 , B64D43/00 , B64D45/00 , G01C17/38 , G01C21/08 , G01C21/165 , G01S19/40
Abstract: An avionics system comprises one or more attitude sources, each configured to produce a respective calculated attitude solution; at least one magnetometer configured to measure magnetic field; and at least one attitude monitor configured to use the respective calculated attitude solution from one of the attitude sources to project the measured magnetic field estimate or an Earth Magnetic Field Model (EMFM) estimate such that the measured magnetic field estimate and the EMFM estimate are in a common shared frame. The at least one attitude monitor is further configured to determine a difference between the measured magnetic field estimate and the EMFM estimate in the common shared frame. The at least one attitude monitor is further configured to output an alert, which indicates that the respective calculated attitude solution used to project the measured magnetic field estimate or the EMFM estimate is in error, if the difference exceeds a predetermined threshold.
-
-
-
-
-
-
-
-
-
Search Results
13
records
(took 0.019 seconds)
