TUHH Open Research
Help
  • Log In
    New user? Click here to register.Have you forgotten your password?
  • English
  • Deutsch
  • Communities & Collections
  • Publications
  • Research Data
  • People
  • Institutions
  • Projects
  • Statistics
  1. Home
  2. TUHH
  3. Publication References
  4. Spectral finite element modeling and updating in aeroelastic analysis of light sport aircraft
 
Options

Spectral finite element modeling and updating in aeroelastic analysis of light sport aircraft

Publikationstyp
Conference Paper
Date Issued
2014
Sprache
English
Author(s)
Gross, Joseph R.  
Weltin, Uwe  
Institut
Zuverlässigkeitstechnik M-24  
TORE-URI
http://hdl.handle.net/11420/7460
Citation
International Forum on Aeroelasticity and Structural Dynamics (IFASD 2013) : Bristol, United Kingdom, 24 - 26 June 2013 / [Royal Aeronautical Society]. - Red Hook, NY : Curran, 2014. - Vols. 1-3 (2014)
Contribution to Conference
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2013  
Scopus ID
2-s2.0-84907322639
Publisher
Curran
In structural dynamics applications, the spectral finite element method (SFEM) can be used to reduce computational expense while calculating spectrally exact solutions to vibration problems. An approach to the application of this method to aeroelastic analysis of light sport aircraft is proposed and investigated. In doing so, certain drawbacks of SFEM are overcome, such as the lack of separate structural operators and the increased difficulty in extracting normal mode shapes from models, which had previously hindered the use of this method in aeroelasticity. A test case in which SFEM is applied to the aeroelastic analysis of a light sport aircraft is used to demonstrate the proposed method. Computational models of the aircraft are derived using SFEM and FEM, then updated to match frequency response data measured in a ground vibration test. Model updating is carried out using a hybrid computational intelligence technique based on the Nelder-Mead simplex algorithm (NMS) in combination with particle swarm optimization (PSO). An accurate match is shown between measured and computed modal results. Modal data from the FE and SFE models is compared to examine differences in accuracy. A flutter calculation is performed with normal modes of the test aircraft found using both methods in order to investigate differences in aeroelastic stability resulting from model deviation. The applicability of the spectral finite element method to aeroelastic analysis of light sport aircraft is assessed ultimately based on a comparison of structural and aeroelastic results found using the standard and spectral finite element methods.
Subjects
Aeroelastic analysis
Ground vibration testing
Spectral finite element method
Structural dynamics
DDC Class
530: Physik
600: Technik
620: Ingenieurwissenschaften
TUHH
Weiterführende Links
  • Contact
  • Send Feedback
  • Cookie settings
  • Privacy policy
  • Impress
DSpace Software

Built with DSpace-CRIS software - Extension maintained and optimized by 4Science
Design by effective webwork GmbH

  • Deutsche NationalbibliothekDeutsche Nationalbibliothek
  • ORCiD Member OrganizationORCiD Member Organization
  • DataCiteDataCite
  • Re3DataRe3Data
  • OpenDOAROpenDOAR
  • OpenAireOpenAire
  • BASE Bielefeld Academic Search EngineBASE Bielefeld Academic Search Engine
Feedback