公开(公告)号：US20160290826A1

公开(公告)日：2016-10-06

申请号：US14564359

申请日：2014-12-09

Applicant: Honeywell International Inc.

Inventor： Mats Anders Brenner ,  Mark A. Ahlbrecht ,  John R. Morrison

IPC: G01C23/00 ,  G07C5/08 ,  G05D1/08 ,  B64D47/00

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。

公开(公告)号：US09435661B2

公开(公告)日：2016-09-06

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

IPC: G01C23/00 ,  B64D45/00 ,  G05D1/08 ,  G07C5/08

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：US20160109233A1

公开(公告)日：2016-04-21

申请号：US14599027

申请日：2015-01-16

Applicant: Honeywell International Inc.

Inventor： John R. Morrison ,  Douglas Mark Weed ,  Mark Hickey

IPC: G01C9/00 ,  G01C17/38 ,  B64D43/00 ,  B64D45/00 ,  G01S19/40

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.

Abstract translation: 航空电子系统包括一个或多个姿态源，每个姿态源被配置为产生相应的计算出的姿态解; 至少一个磁力计被配置成测量磁场; 以及至少一个姿态监视器，被配置为使用来自姿态源中的一个的相应计算的姿态解决方案来投影测量的磁场估计或地磁场模型（EMFM）估计，使得测量的磁场估计和EMFM估计在 一个共同的共享框架。 所述至少一个姿态监视器还被配置为确定所述公共共享帧中所测量的磁场估计与所述EMFM估计之间的差异。 所述至少一个姿态监视器还被配置为输出警报，其指示如果所述差超过预定阈值，则指示用于投影所测量的磁场估计或所述EMFM估计的所计算的姿态解决方案是错误的。