• Title/Summary/Keyword: 레벤버그-마쿼트 알고리듬

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Laplace-domain Waveform Inversion using the Pseudo-Hessian of the Logarithmic Objective Function and the Levenberg-Marquardt Algorithm (로그 목적함수의 유사 헤시안을 이용한 라플라스 영역 파형 역산과 레벤버그-마쿼트 알고리듬)

  • Ha, Wansoo
    • Geophysics and Geophysical Exploration
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    • v.22 no.4
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    • pp.195-201
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    • 2019
  • The logarithmic objective function used in waveform inversion minimizes the logarithmic differences between the observed and modeled data. Laplace-domain waveform inversions usually adopt the logarithmic objective function and the diagonal elements of the pseudo-Hessian for optimization. In this case, we apply the Levenberg-Marquardt algorithm to prevent the diagonal elements of the pseudo-Hessian from being zero or near-zero values. In this study, we analyzed the diagonal elements of the pseudo-Hessian of the logarithmic objective function and showed that there is no zero or near-zero value in the diagonal elements of the pseudo-Hessian for acoustic waveform inversion in the Laplace domain. Accordingly, we do not need to apply the Levenberg-Marquardt algorithm when we regularize the gradient direction using the pseudo-Hessian of the logarithmic objective function. Numerical examples using synthetic and field datasets demonstrate that we can obtain inversion results without applying the Levenberg-Marquardt method.

Model-Reference Adaptive Pitch Attitude Control of Fixed-Wing UAV (고정익 무인 항공기 피치 자세의 모델-참조 적응 제어)

  • Kim, Byung-Wook;Park, Sang-Hyuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.47 no.7
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    • pp.499-507
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    • 2019
  • Despite the well-known mathematical model of fixed-wing aircraft, there are various studies to meet desired performances by considering the modeling errors in the extended flight envelope. This paper proposes a new adaptation mechanism of model-reference adaptive control, which applies the Levenberg-Marquardt algorithm to the pitch attitude control of fixed-wing UAV. In addition, reference model in the adaptation law is set by referring to the dynamic properties of the plant model. The performance of the proposed adaptive control law is verified through simulations and flight tests.