Experimental Modal Analysis of a Half-Scale Model Rear Twin-Engine Mounted Aircraft Fuselage Section
Loading...
Authors
Chamberlain, Diego
Date
Type
thesis
Language
eng
Keyword
Modal Analysis , Aircraft , Noise , Vibration
Alternative Title
Abstract
Experimental modal testing using an impact hammer is a commonly used method for obtaining the modal parameters of any structure for which the vibrational behavior is of interest. Natural frequencies and associated mode shapes of the structure can be extracted directly from measured FRFs (Frequency Response Functions) through various curve fitting procedures. This thesis provides an overview of the modal testing conducted on various scaled aerospace components. These components are part of a half-scale model rear twin-engine mounted aircraft fuselage tail section which is being constructed in order to provide relevant vibrational and dynamic trends to a leading Canadian aerospace manufacturer. The experimental modal results were used to validate the associated computational modal data. It is this initial validation step which forms the foundation of the research project presented herein and which will allow for future modal testing work to be conducted on the half-scale assembly once completed. Testing set-up, experimental equipment and the methodology employed are all described in detail. Furthermore, a series of validity checks were done by ensuring that the experimental results satisfy the requirements inherent to linear modal analysis including repeatability, reciprocity and linearity. This provided confidence in the employed testing procedure. Recorded natural frequencies (eigenvalues), mode shapes (eigenvectors), coherence plots and other important experimental data are presented along with notable trends. Finally, key literature has been referenced where appropriate and important concepts to modal analysis are expanded upon. This thesis, then, demonstrates that experimental modal analysis can be successfully implemented into a testing methodology that helps establish vibrational trends and, thus, better understand and help resolve vibro-acoustic issues on aircraft.
Description
Citation
Publisher
License
Attribution-NonCommercial-NoDerivs 3.0 United States
Queen's University's Thesis/Dissertation Non-Exclusive License for Deposit to QSpace and Library and Archives Canada
ProQuest PhD and Master's Theses International Dissemination Agreement
Intellectual Property Guidelines at Queen's University
Copying and Preserving Your Thesis
This publication is made available by the authority of the copyright owner solely for the purpose of private study and research and may not be copied or reproduced except as permitted by the copyright laws without written authority from the copyright owner.
Queen's University's Thesis/Dissertation Non-Exclusive License for Deposit to QSpace and Library and Archives Canada
ProQuest PhD and Master's Theses International Dissemination Agreement
Intellectual Property Guidelines at Queen's University
Copying and Preserving Your Thesis
This publication is made available by the authority of the copyright owner solely for the purpose of private study and research and may not be copied or reproduced except as permitted by the copyright laws without written authority from the copyright owner.