Output Error Method for Tiltrotor Unstable in Hover

• Autorzy: Lichota P. , Szulczyk J.

Identyfikatory

DOI

10.1515/meceng-2017-0002

• Języki publikacji: EN

Abstrakty

EN

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.

Słowa kluczowe

EN

flight dynamics; system identification; output error method; maximum likelihood; unstable system; tiltrotor

PL

dynamika lotu; identyfikacja systemu; metoda błędu wyjścia; maksymalne prawdopodobieństwo; system niestabilny; zmiennopłat

• Wydawca: Komitet Budowy Maszyn PAN
• Czasopismo: Archive of Mechanical Engineering
• Rocznik: 2017
• Tom: Vol. LXIV, nr 1
• Strony: 23--36
• Opis fizyczny: Bibliogr. 21 poz., rys., tab.

Twórcy

autor

Lichota P.

• Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics, Poland

autor

Szulczyk J.

• Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics, Poland

Bibliografia

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Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).