Ground vibration test identified structure model for flutter envelope prediction

Jie Zeng, P. C. Chen, Erich Ritz, Dallas W. Kingsbury, Marc Mignolet, Starr Ginn

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

3 Scopus citations

Abstract

In this paper, a new technique is introduced for the determination of the flutter speed and frequency of vehicles or wings. Instead of using the finite element modeling, the structural model which is directly estimated / identified from the ground vibration test of the real structure is implemented for flutter prediction. The advantage of using the estimated structural model is that the structural damping is included for the flutter prediction, and thereafter, a more reasonable flutter solution shall be obtained. With the computation of the unsteady aerodynamic reduced order model, and the correct coupling of the estimated structural model, a time domain flutter analysis can be readily performed. The proposed new technique will demonstrated using the NASA Langley Paddle wing structure.

Original languageEnglish (US)
Title of host publicationAIAA Atmospheric Flight Mechanics Conference 2012
DOIs
StatePublished - 2012
EventAIAA Atmospheric Flight Mechanics Conference 2012 - Minneapolis, MN, United States
Duration: Aug 13 2012Aug 16 2012

Publication series

NameAIAA Atmospheric Flight Mechanics Conference 2012

Other

OtherAIAA Atmospheric Flight Mechanics Conference 2012
CountryUnited States
CityMinneapolis, MN
Period8/13/128/16/12

ASJC Scopus subject areas

  • Computer Science Applications
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering

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