Aerospace Science and Technology
Different approaches for the estimation of the states of linear dynamic systems are commonly used, the most common being the Kalman filter. For nonlinear systems, variants of the Kalman filter are used. Some of these variants include the LKF (linearized Kalman filter), the EKF (extended Kalman filter), and the UKF (unscented Kalman filter). With the LKF and EKF, performance varies depending on how often Jacobians (partial derivative matrices) are updated. In other words, we see a tradeoff between computational effort and filtering performance. With the unscented Kalman filter, Jacobians are not calculated but computational effort is typically high due to the need for multiple simulations at each time step of the underlying dynamic system. Up to this point in time a number of filtering approaches have been used for aircraft turbofan engine health estimation, but a systematic comparison has not been published. This paper compares the estimation accuracy and computational effort of these filters for aircraft engine health estimation. We show in this paper that the EKF and UKF both outperform the LKR The EKF computational effort is an order of magnitude higher than the LKF, and the UKF is another order of magnitude higher than the EKE Overall we conclude that the EKF, with Jacobian calculations about every three flights, is the best choice for aircraft engine health estimation. (C) 2007 Elsevier Masson SAS. All rights reserved.
Simon, Daniel J., "A Comparison of Filtering Approaches for Aircraft Engine Health Estimation" (2008). Electrical Engineering and Computer Science Faculty Publications. 25.
Simon, D. (2008). A comparison of filtering approaches for aircraft engine health estimation. Aerospace Science and Technology, 12(4), 276-284.
NOTICE: this is the author’s version of a work that was accepted for publication in Aerospace Science and Technology. Changes resulting from the publishing process, such as peer review, editing, corrections, structural formatting, and other quality control mechanisms may not be reflected in this document. Changes may have been made to this work since it was submitted for publication. A definitive version was subsequently published in Aerospace Science and Technology, 12, 4, (01-01-2008); 10.1016/j.ast.2007.06.002
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