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    Wyświetlanie 1-4 z 4
    Tytuł:
    Inclusion of the D-optimality in multisine manoeuvre design for aircraft parameter estimation
    Autorzy:
    Lichota, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/281598.pdf
    Data publikacji:
    2016
    Wydawca:
    Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
    Tematy:
    inputs design
    system identification
    flight dynamics
    Opis:
    This paper is concerned with the designing of simultaneous flight control deflections for aircraft system identification. The elevator, ailerons and rudder are excited with harmonically related multisine signals. The optimal deflections are designed when there is no information about the stability and control derivatives and when this information is available. The inclusion of the system dynamics in the inputs design phase is done with the D-optimality criterion. Both sets of optimal flight surface deflections are used as excitations of a nonlinear aircraft model which is identified through the maximum likelihood estimation method. Parameters accuracy for those maneuvers (designed with and without a-priori knowledge) is presented and compared.
    Źródło:
    Journal of Theoretical and Applied Mechanics; 2016, 54, 1; 87-98
    1429-2955
    Pojawia się w:
    Journal of Theoretical and Applied Mechanics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Power spectrum optimization in the design of multisine manoeuvre for identification purposes
    Autorzy:
    Lichota, P.
    Szulczyk, J.
    Noreña, D. A.
    Vallejo Monsalve, F. A.
    Powiązania:
    https://bibliotekanauki.pl/articles/279485.pdf
    Data publikacji:
    2017
    Wydawca:
    Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
    Tematy:
    flight dynamics
    optimal input design
    multisine excitations
    system identification
    least squares
    maximum likelihood
    Opis:
    In this paper, two sets of multisine signals are designed for system identification purposes. The first one is obtained without any information about system dynamics. In the second case, the a priori information is given in terms of dimensional stability and control derivatives. Magnitude Bode plots are obtained to design the multisine power spectrum that is optimized afterwards. A genetic algorithm with linear ranking, uniform crossover and mutation operator has been employed for that purpose. Both designed manoeuvres are used to excite the aircraft model, and then system identification is performed. The estimated parameters are obtained by applying two methods: Equation Error and Output Error. The comparison of both investigated cases in terms of accuracy and manoeuvre time is presented afterwards.
    Źródło:
    Journal of Theoretical and Applied Mechanics; 2017, 55, 4; 1193-1203
    1429-2955
    Pojawia się w:
    Journal of Theoretical and Applied Mechanics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Output Error Method for Tiltrotor Unstable in Hover
    Autorzy:
    Lichota, P.
    Szulczyk, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/140298.pdf
    Data publikacji:
    2017
    Wydawca:
    Polska Akademia Nauk. Czytelnia Czasopism PAN
    Tematy:
    flight dynamics
    system identification
    output error method
    maximum likelihood
    unstable system
    tiltrotor
    dynamika lotu
    identyfikacja systemu
    metoda błędu wyjścia
    maksymalne prawdopodobieństwo
    system niestabilny
    zmiennopłat
    Opis:
    This article investigates unstable tiltrotor in hover system identification from flight test data. The aircraft dynamics was described by a linear model defined in Body-Fixed-Coordinate System. Output Error Method was selected in order to obtain stability and control derivatives in lateral motion. For estimating model parameters both time and frequency domain formulations were applied. To improve the system identification performed in the time domain, a stabilization matrix was included for evaluating the states. In the end, estimates obtained from various Output Error Method formulations were compared in terms of parameters accuracy and time histories. Evaluations were performed in MATLAB R2009b environment.
    Źródło:
    Archive of Mechanical Engineering; 2017, LXIV, 1; 23-36
    0004-0738
    Pojawia się w:
    Archive of Mechanical Engineering
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Aircraft dynamic model identification on the basis of flight data recorder registers
    Autorzy:
    Lasek, L.
    Lichota, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/115522.pdf
    Data publikacji:
    2013
    Wydawca:
    Fundacja na Rzecz Młodych Naukowców
    Tematy:
    Dimensional derivatives
    estimation
    Flight Data Recorder
    Flight Dynamics
    Maximum Likelihood Estimation
    Levenberg-Marquardt
    System Identification
    Opis:
    We investigate the problem of an aircraft dynamic model parametric identification using dimensional derivatives as an example. Identification is done in offline mode, in the time domain. Flight parameters used for identification are obtained from Flight Data Recorder, that register them during each scheduled flight. We investigate the possibility of application of Maximum Likelihood Estimation that belongs to the Output Error Methods class. The likelihood function is defined for n-dimensional multivariate normal distribution. Unknown covariance matrix is estimated with the use of measured data and output equation. Output equation is calculated with Runge–Kutta fourth order method. In order to find the cost function minimum we consider using Levenberg-Marquardt Algorithm, where derivatives are calculated with central difference formulas and small perturbations theory. Mathematical model of an aircraft is obtained through flight dynamics classical approach. Rigid body model of an aircraft is assumed. Coordinate Systems Transformations are done using Euler’s Rotation Theorem with angle order typical for flight dynamics. Equations of motion are obtained from Newtons Second Law of Motion in body fixed coordinate system Oxyz, that is located at aircraft’s center of gravity. Turbulence is modeled as a bias, and also is an object of identification. We implement this method in Matlab R2009b environment.
    Źródło:
    Challenges of Modern Technology; 2013, 4, 1; 16-20
    2082-2863
    2353-4419
    Pojawia się w:
    Challenges of Modern Technology
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-4 z 4

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