Structural model identification of a small flexible aircraft

Author

Moreno, Claudia P. ; Gupta, Arpan ; Pfifer, Harald ; Taylor, B. ; Balas, Gary J.

Author_Institution

Dept. of Aerosp. Eng. & Mech., Univ. of Minnesota, Minneapolis, MN, USA

fYear

2014

fDate

4-6 June 2014

Firstpage

4379

Lastpage

4384

Abstract

The system identification of a light-weight, high-aspect ratio wing is presented. Experimental data is obtained from a ground vibration test. The input signals are sine sweep wave forces and the outputs are the corresponding acceleration responses of the aircraft. Subspace algorithms are used to estimate a state-space model of the aircraft. Minimization of the model prediction error is performed to fit the frequency response data. As result, the estimated model identifies six structural modes between 5 Hz and 30 Hz.

Keywords

aerospace components; aircraft; dynamic testing; flexible structures; frequency response; identification; state-space methods; vibrations; frequency response data; ground vibration test; high-aspect ratio wing; lightweight ratio wing; model prediction error minimization; sine sweep wave; small flexible aircraft; state-space model estimation; structural model identification; system identification; Aircraft; Atmospheric modeling; Data models; Frequency measurement; Frequency response; Mathematical model; State-space methods; Flexible structures; Identification; Linear systems;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference (ACC), 2014

Conference_Location

Portland, OR

ISSN

0743-1619

Print_ISBN

978-1-4799-3272-6

Type

conf

DOI

10.1109/ACC.2014.6859471

Filename

6859471