| 多操纵面飞机舵面损伤的快速故障诊断 |
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| 引用本文： | 王发威,董新民,陈勇,王小平,廖开俊. 多操纵面飞机舵面损伤的快速故障诊断[J]. 航空学报, 2015, 36(7): 2350-2360. DOI: 10.7527/S1000-6893.2015.0009 |
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| 作者姓名： | 王发威 董新民 陈勇 王小平 廖开俊 |
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| 作者单位： | 1. 空军工程大学 航空航天工程学院, 西安 710038;2. 空军第一航空学院 航空仪电工程系, 信阳 464000 |
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| 基金项目： | 国家自然科学基金 (61304120) |
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| 摘 要： | 针对多操纵面飞机舵面损伤的快速故障诊断问题,提出一种直接估计舵面偏转量的自适应补偿观测器方法。首先,设计了增广观测器进行系统输入估计,并提出了自适应补偿方法解决其动态跟踪性能差的问题;其次,设计了一种新的自适应阈值以快速检测故障并降低虚警率;最后,利用舵面故障特点,采用重置初值的限定记忆最小二乘方法实现了对突变参数的实时估计,用以进行故障隔离。仿真结果表明:在不同的舵面损伤故障情况下,所提出的观测器方法能在20 ms内发出故障预警,并在0.22 s内确定故障位置,所采用的辨识方法可以在故障报警后的0.2 s内准确估计出损伤程度。
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| 关 键 词： | 多操纵面飞机 舵面损伤 故障诊断 自适应阈值 参数估计 |
| 收稿时间： | 2014-05-29 |
| 修稿时间： | 2015-01-07 |
Fast fault diagnosis of multi-effectors aircraft with control surface damage |
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| WANG Fawei,DONG Xinmin,CHEN Yong,WANG Xiaoping,LIAO Kaijun. Fast fault diagnosis of multi-effectors aircraft with control surface damage[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7): 2350-2360. DOI: 10.7527/S1000-6893.2015.0009 |
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| Authors: | WANG Fawei DONG Xinmin CHEN Yong WANG Xiaoping LIAO Kaijun |
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| Affiliation: | 1. Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;2. Department of Aeronautic Instrument Electrical Engineering, First Aeronautical College of Air Force, Xinyang 464000, China |
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| Abstract: | An adaptive compensation observer is presented for fast fault diagnosis of multi-effectors aircraft in the presence of control surface damage, which directly estimates the deflection angles of control surfaces. Firstly, an augmented observer is designed for the estimation of system input and an adaptive compensation is introduced to improve the dynamic tracking performance of observer. Secondly, new adaptive thresholds are designed for the fast fault detection and reduction of the false alarm rate. Finally, the actuator fault feature of control surface is employed to reset the initial conditions. The limited memory least square method is developed to achieve a real-time estimation of mutation parameters, which is applied for fault isolation. Simulation results suggest that in different cases of actuator faults of control surface damage, the proposed observer methods can achieve fault alarm within 20 ms and determine the fault location in 0.22 s. Furthermore, the identification method can accurately estimate the degree of damaging within 0.2 s after fault alarm. |
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| Keywords: | multi-effectors aircraft control surface damage fault diagnosis adaptive threshold parameter estimation |
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