A Note on Flight Flutter Testing

1948 ◽  
Vol 15 (6) ◽  
pp. 366-370 ◽  
Author(s):  
ROBERT ROSENBAUM ◽  
ROBERT H. SCANLAN
Keyword(s):  
Flutter Testing

scholarly journals A method for identification of non-linear multi-degree-of-freedom systems

1998 ◽  
Vol 212 (4) ◽  
pp. 287-298 ◽  
Author(s):  
G Dimitriadis ◽  
J E Cooper
Keyword(s):  
System Identification ◽  
Degree Of Freedom ◽  
Accurate Identification ◽  
Wide Range ◽  
Non Linear ◽  
Linear System Identification ◽  
The Stability ◽  
Non Linear System ◽  
Identification Techniques ◽  
Flutter Testing

System identification methods for non-linear aeroelastic systems could find uses in many aeroelastic applications such as validating finite element models and tracking the stability of aircraft during flight flutter testing. The effectiveness of existing non-linear system identification techniques is limited by various factors such as the complexity of the system under investigation and the type of non-linearities present. In this work, a new approach is introduced which can identify multi-degree-of-freedom systems featuring any type of non-linear function, including discontinuous functions. The method is shown to yield accurate identification of three mathematical models of aeroelastic systems containing a wide range of structural non-linearities.

An application of system identification to flutter testing

1980 ◽  
Vol 72 (2) ◽  
pp. 141-150 ◽  
Author(s):  
D.R. Gaukroger ◽  
C.W. Skingle ◽  
K.H. Heron
Keyword(s):  
System Identification ◽  
Flutter Testing

scholarly journals Real-time modal analysis and its application for flutter testing

2003 ◽  
Vol 36 (16) ◽  
pp. 687-692 ◽  
Author(s):  
Tadeusz Uhl ◽  
Mariusz Bogacz
Keyword(s):  
Modal Analysis ◽  
Real Time ◽  
Flutter Testing

Supersonic Unstalled Flutter In Fan Rotors; Analytical and Experimental Results

1974 ◽  
Vol 96 (4) ◽  
pp. 379-386 ◽  
Author(s):  
L. E. Snyder ◽  
G. L. Commerford
Keyword(s):  
Wind Tunnel ◽  
High Speed ◽  
Reduced Frequency ◽  
Cascade Analysis ◽  
Blade Shape ◽  
Supersonic Flutter ◽  
Transonic Fan ◽  
Flutter Testing ◽  
Stagger Angle ◽  
Interblade Phase Angle

Supersonic unstalled flutter is predicted using an unsteady supersonic cascade analysis, a cascade wind tunnel and a high speed fan rotor. Since the unsteady analysis assumes thin flat plate airfoils, the effect of thickness and blade shape was examined experimentally by flutter testing two sets of supersonic blading in a cascade wind tunnel. The effects of changes in Mach number, reduced frequency, stagger angle and interblade phase angle were examined from the analysis and tests. Results show that the trends are in agreement, but that blade shape has an effect on the level of reduced velocity at the incipient flutter point. The unsteady aerodynamic analysis is applied to two transonic fan stages. The first rotor was designed as a supersonic flutter test vehicle while the second was designed to be flutter free. Results of the fan tests show that the analysis correctly predicts the susceptibility to flutter of each rotor.

scholarly journals Transmissibilty-Based Operational Modal Analysis for Flight Flutter Testing Using Exogenous Inputs

2012 ◽  
Vol 19 (5) ◽  
pp. 1071-1083 ◽  
Author(s):  
Christof Devriendt ◽  
Tim De Troyer ◽  
Gert De Sitter ◽  
Patrick Guillaume
Keyword(s):  
Modal Analysis ◽  
Frequency Domain ◽  
Experimental Modal Analysis ◽  
Operational Modal Analysis ◽  
Modal Parameters ◽  
Input Output ◽  
Output Only ◽  
Flutter Testing

During the recent years several new tools have been introduced by the Vrije Universiteit Brussel in the field of Operational Modal Analysis (OMA) such as the transmissibility based approach and the the frequency-domain OMAX concept. One advantage of the transmissibility based approach is that the ambient forces may be coloured (non-white), if they are fully correlated. The main advantage of the OMAX concept is the fact that it combines the advantages of Operational and Experimental Modal Analysis: ambient (unknown) forces as well as artificial (known) forces are processed simultaneously resulting in improved modal parameters. In this paper, the transmissibility based output-only approach is combined with the input/output OMAX concept. This results in a new methodology in the field of operational modal analysis allowing the estimation of (scaled) modal parameters in the presence of arbitrary ambient (unknown) forces and artificial (known) forces.

Sign in / Sign up

Export Citation Format

Share Document