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Warianty tytułu
Języki publikacji
Abstrakty
The electromechanical actuator (EMA) model is presented with the methods for identifying its design parameters. The actuator is a part of the system for flap deployment on the commercial transport airplane. The differential equations with the feedback control describe behaviour of the actuator deflection. There are two concepts of drive system simultaneously considered: a high torque/low speed (HT/LS) and a geared low torque/high speed (LT/HS). For parameter identification in both cases the Maximum Likelihood (ML) method with two minimisation algorithms: linearized Gauss-Newton and Levenberg-Marquardt is applied. Both approaches for each of two design solutions were effective, while tested on hypothetical data.
Rocznik
Tom
Strony
35--40
Opis fizyczny
Bibliogr. 5 poz., rys.
Twórcy
autor
autor
- Ph.D. Student, Department of Automation and Aeronautical Systems, Warsaw University of Technology, Warsaw, 00-665, Poland, martyna.ulinowicz@meil.pw.edu
Bibliografia
- [1] Andrzejczak M., Methods applied to aircraft identification, III International Conference “Intelligence, Integration, Reliability” papers, Kijev, 2010.
- [2] Bonnas J.F., Numerical optimization: Theoretical and practical aspects, Springer-Verlag: Berlin, 2006.
- [3] Esfandiari R.S., Bei L., Modeling and analysis of dynamic systems, CRC Press/Taylor& Francis Group: Boca Raton, 2010.
- [4] Jategaonkar, Ravindra V., Flight vehicle system identification, A Time Domain Methodology, American Institute of Aeronautics and Astronautics, Reston, Virginia, 2006.
- [5] New Track integrated Electrical Single Flap Drive System (NEFS), 6th European Union Framework Programme research project, http://www.nefs.eu/
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BUJ8-0007-0006