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Inventi Impact - Aerospace Engineering

Articles

  • Inventi:eae/58/14
    ACTUATOR FAULT DIAGNOSIS IN A BOEING 747 MODEL VIA ADAPTIVE MODIFIED TWO-STAGE KALMAN FILTER
    Fikret Caliskan, Youmin Zhang, N Eva Wu, Jong-Yeob Shin

    An adaptive modified two-stage linear Kalman filtering algorithm is utilized to identify the loss of control effectiveness and the magnitude of low degree of stuck faults in a closed-loop nonlinear B747 aircraft. Control effectiveness factors and stuck magnitudes are used to quantify faults entering control systems through actuators. Pseudorandomexcitation inputs are used to help distinguish partial loss and stuck faults. The partial loss and stuck faults in the stabilizer are isolated and identified successfully.

    How to Cite this Article
    CC Compliant Citation: Fikret Caliskan, Youmin Zhang, N. Eva Wu, and Jong-Yeob Shin, “Actuator Fault Diagnosis in a Boeing 747 Model via Adaptive Modified Two-Stage Kalman Filter,” International Journal of Aerospace Engineering, vol. 2014, Article ID 472395, 10 pages, 2014. doi:10.1155/2014/472395. Copyright © 2014 Fikret Caliskan et al. This is an open access article distributed under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0/), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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