Structural model identification of a small flexible aircraft

Claudia P. Moreno, Abhineet Gupta, Harald Pfifer, Brian Taylor, Gary J. Balas

Research output: Chapter in Book/Report/Conference proceedingConference contribution

17 Scopus citations


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.

Original languageEnglish (US)
Title of host publication2014 American Control Conference, ACC 2014
PublisherInstitute of Electrical and Electronics Engineers Inc.
Number of pages6
ISBN (Print)9781479932726
StatePublished - 2014
Event2014 American Control Conference, ACC 2014 - Portland, OR, United States
Duration: Jun 4 2014Jun 6 2014

Publication series

NameProceedings of the American Control Conference
ISSN (Print)0743-1619


Other2014 American Control Conference, ACC 2014
Country/TerritoryUnited States
CityPortland, OR


  • Flexible structures
  • Identification
  • Linear systems


Dive into the research topics of 'Structural model identification of a small flexible aircraft'. Together they form a unique fingerprint.

Cite this