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Evaluation of Sensor Failure Detection, Identification and Accommodation (SFDIA) Performance following Common-Mode Failures of Pitot Tubes

机译:在Pitot管的共模故障后,评估传感器故障检测,识别和住宿(SFDIA)性能

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Recent catastrophic air crashes have shown that physical redundancy is not a foolproof option for failures on Air Data Systems (ADS) on an aircraft providing airspeed measurements. Since all the redundant sensors are subjected to the same environmental conditions in flight, a failure on one sensor could occur on the other sensors under certain conditions such as extreme weather; this class of failure is known in the literature as "common mode" failure. In this paper, different approaches to the problem of detection, identification and accommodation of failures on the Air Data System (ADS) of an aircraft are evaluated. This task can be divided into component tasks of equal criticality as Sensor Failure Detection and Identification (SFDI) and Sensor Failure Accommodation (SFA). Data from flight test experiments conducted using the WVU YF-22 unmanned research aircraft are used. Analytical redundancy is provided through a least squares modeling based approach and an extended Kalman filter approach to handle the Sensor Failure Accommodation (SFA) task. From experiments, it is seen that both these approaches provide reasonable estimates of airspeed with an average estimation error of 0.533 m/s and standard deviation of 1.6446 m/s. Furthermore two approaches to the task of Sensor Failure Detection and Identification (SFDI) based on different fault detection filters were evaluated. A Cumulative Sum (CUSUM) detector and the Generalized Likelihood Ratio Test (GLRT) detector were evaluated for different failure conditions - a sudden step bias, a fast rising fault and a slow rising fault in the measured airspeed and compared in terms of sensitivity to the failure magnitude, detection delay, false alarms and undetected faults. It was determined that on an average, the CUSUM filter performed slightly better in terms of detecting failures than the GLRT based detection for the given set of data.
机译:最近的灾难性空气崩溃表明,用于在提供空速测量的飞机上的空中数据系统(广告)上的故障方面的冗余选择是一种万无一失的选择。由于所有冗余传感器在飞行中进行了相同的环境条件,因此在极端天气之类的某些条件下,在其他传感器上可能发生一个传感器的故障;这类失败在文献中已知为“共模”故障。在本文中,评估了飞机的空气数据系统(ADS)上的检测,识别和对失败的问题的不同方法。该任务可分为等于临界的组件任务,作为传感器故障检测和识别(SFDI)和传感器故障住宿(SFA)。使用使用WVU YF-22无人赛研究飞机进行的飞行试验实验的数据。分析冗余通过基于最小二乘建模的方法和扩展卡尔曼滤波器方法提供,以处理传感器故障容纳(SFA)任务。从实验开始,看出,这两种方法都提供了对空速的合理估计,平均估计误差为0.533 m / s,标准差为1.6446 m / s。此外,评估了基于不同故障检测滤波器的传感器故障检测和识别(SFDI)任务的两种方法。评估累积和探测器和广义似然比测试(GLRT)检测器对不同的故障条件进行评估 - 突然步骤偏置,在测量的空速中的快速上升故障和慢上升的故障,并在对敏感性方面进行比较故障幅度,检测延迟,误报和未检测到的故障。确定在平均而言,在检测到给定数据集的GLRT的检测方面,CUSUM滤波器略微更好地执行。

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