The paper discusses the application of a FEM model updating technique, based on a forward sensitivity formulation, to a twin propeller commuter aircraft. The applied updating technique varies the mass and stiffness characteristics of the FEM model so that predicted system performance, in terms of modal parameters, matches the measured system performance from a Ground Vibration Test. The variations of the mass and stiffness characteristics are realized by proportional changes of the FEM element mass and stiffness matrices, thereby disturbing the original structure of the FEM model as little as possible. Proportional changes of groups of elements can be linked in one variable, and interpreted in terms of variations in corresponding element material or geometry characteristics. The model updating technique is applied to improve the dynamic model of a BOEING DeHaviland DASH8-300A aircraft based on data from a Ground Vibration Test. A correlation analysis followed by FEM updating resulted in a closer fit of the analytial and experimental modal parameters. The different steps in this updating procedure, leading to a more reliable model for further analytical flutter analysis, are discussed in detail.
Application of FEM model correlation and updating techniques on an aircraft using test data of a ground vibration survey
Anwendung eines Verfahrens zur Überprüfung und Anpassung der FEM-Modellparameter eines Flugzeuges unter Nutzung von Testdaten aus einer Vibrationsuntersuchung am Boden
IMAC, Proc. of the 9th Int. Modal Analysis, Conf. ; 1 ; 517-525
1991
9 Seiten, 11 Bilder, 1 Tabelle, 4 Quellen
Conference paper
English
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