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A semi-analytical approach for flutter analysis of a high-aspect-ratio wing

Published online by Cambridge University Press:  07 August 2020

R.F. Latif ,
M.K.A. Khan Open the ORCID record for M.K.A. Khan [Opens in a new window] ,
A. Javed ,
S.I.A. Shah  and
S.T.I. Rizvi
R.F. Latif
Affiliation:
CAE, National University of Sciences and Technology (NUST), Department of Aerospace Engineering, Islamabad, Pakistan
M.K.A. Khan*
Affiliation:
CAE, National University of Sciences and Technology (NUST), Department of Aerospace Engineering, Islamabad, Pakistan
A. Javed
Affiliation:
CAE, National University of Sciences and Technology (NUST), Department of Aerospace Engineering, Islamabad, Pakistan
S.I.A. Shah
Affiliation:
CAE, National University of Sciences and Technology (NUST), Department of Aerospace Engineering, Islamabad, Pakistan
S.T.I. Rizvi
Affiliation:
Air University, Aerospace and Aviation Campus, Kamra, Pakistan
*
[email protected]
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Abstract

We present a hybrid, semi-analytical approach to perform an eigenvalue-based flutter analysis of an Unmanned Aerial Vehicle (UAV) wing. The wing has a modern design that integrates metal and composite structures. The stiffness and natural frequency of the wing are calculated using a Finite Element (FE) model. The modal parameters are extracted by applying a recursive technique to the Lanczos method in the FE model. Subsequently, the modal parameters are used to evaluate the flutter boundaries in an analytical model based on the p-method. Two-degree-of-freedom bending and torsional flutter equations derived using Lagrange’s principle are transformed into an eigenvalue problem. The eigenvalue framework is used to evaluate the stability characteristics of the wing under various flight conditions. An extension of this eigenvalue framework is applied to determine the stability boundaries and corresponding critical flutter parameters at a range of altitudes. The stability characteristics and critical flutter speeds are also evaluated through computational analysis of a reduced-order model of the wing in NX Nastran using the k- and pk-methods. The results of the analytical and computational methods are found to show good agreement with each other. A parametric study is also carried out to analyse the effects of the structural member thickness on the wing flutter speeds. The results suggest that changing the spar thickness contributes most significantly to the flutter speeds, whereas increasing the rib thickness decreases the flutter speed at high thickness values.

Keywords

AeroelasticityFlutterFinite element modellingHigh aspect ratioReduced order modelUAV
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1284 , February 2021 , pp. 410 - 429
Copyright
© The Author(s), 2020. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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