TY - GEN
T1 - Ground vibration test identified structure model for flutter envelope prediction
AU - Zeng, Jie
AU - Chen, P. C.
AU - Ritz, Erich
AU - Kingsbury, Dallas W.
AU - Mignolet, Marc
AU - Ginn, Starr
N1 - Funding Information:
This research is supported by NASA Dryden Flight Research Center under a Small Innovation Research (STTR) Phase II contract NNX09CB63C.
PY - 2012
Y1 - 2012
N2 - 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.
AB - 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.
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U2 - 10.2514/6.2012-4856
DO - 10.2514/6.2012-4856
M3 - Conference contribution
AN - SCOPUS:84880787951
SN - 9781624101847
T3 - AIAA Atmospheric Flight Mechanics Conference 2012
BT - AIAA Atmospheric Flight Mechanics Conference 2012
T2 - AIAA Atmospheric Flight Mechanics Conference 2012
Y2 - 13 August 2012 through 16 August 2012
ER -