Fault diagnosis for nonlinear aircraft based on control-induced redundancy
Fault diagnosis for nonlinear aircraft based on control-induced redundancy
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DOI：
10.1109/systol.2010.5676073
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发表时间：
2010-12
期刊：
影响因子：
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通讯作者：
J. Marzat;H. Piet-Lahanier;F. Damongeot;E. Walter
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文献类型：
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作者：
J. Marzat;H. Piet-Lahanier;F. Damongeot;E. Walter
提出了一种通用三维飞行器故障检测与隔离方法。飞机的行为是由一个非线性控制仿射模型，这是闭环控制的经典制导，导航和控制（GNC）算法。建议的FDI程序利用该控制模块引起的冗余，沿着由惯性测量单元（IMU）测量的加速度。因此，一些状态变量的一阶导数的估计是容易获得的，并且允许人们估计由致动器实现的控制输入。由于发送到致动器的计算的控制输入是已知的，因此可以使用这两个元素之间的差异作为故障的残差指示。该策略成功地应用于拟议的航空基准检测和隔离执行器故障，同时影响飞行控制面和推进。
A Fault Detection and Isolation (FDI) method for a generic 3D aircraft is presented. The behavior of the aircraft is described by a nonlinear control-affine model, which is closed-loop controlled by a classical guidance, navigation and control (GNC) algorithm. The proposed FDI procedure exploits the redundancy induced by this control module, along with the accelerations measured by the Inertial Measurement Unit (IMU). Estimates of first-order derivatives of some state variables are thus readily available and allow one to estimate the control inputs as achieved by the actuators. Since the computed control input sent to the actuator is known, it is possible to use the discrepancy between these two elements as a residual indicative of faults. This strategy is successfully applied to the proposed aeronautical benchmark to detect and isolate actuator faults affecting simultaneously flight control surfaces and propulsion.